RU2474862C1 - Flight director display - Google Patents

Abstract

FIELD: physics.

SUBSTANCE: invention relates to information display apparatus used by a pilot and crew members when piloting aircraft, and specifically to flight director displays with display of "Leader" and "Airplane" indices. The flight director display is further provided with units to whose inputs are transmitted signals from the aircraft systems: a unit for calculating parameters of the current yaw angle, a unit for calculating the value of the calculated banking angle, a unit for calculating the calculated yaw angle, a unit for calculating deviation of the aircraft on flight altitude and the scale factor of the deviation of the flight altitude of the aircraft, a unit for calculating the value of the calculated pitch angle, a unit for calculating lateral deviation and the scale factor of lateral deviation of the aircraft, wherein outputs are connected to inputs of a character generator.

EFFECT: preventing piloting errors, emergency and catastrophic consequences of flying associated with the pilot losing spatial orientation due to formation, on the display field of the screen of the flight director display, a complexity of the current information on roll-pitch-altitude-yaw at the same time.

3 cl, 21 dwg

Description

The invention relates to devices for displaying information used by the pilot and crew when piloting aircraft (LA), and in particular to flight control indicators (KPI).

The closest in technical essence to the claimed technical solution is the “Flight-pilot indicator”, RF Patent No. 2207514 dated 01/10/2002 IPC G01C 23/00 /, in which

on the front of the screen are:

- scale of vertical speed;

- indication of autopilot modes;

- various navigation information, in particular the image of the planning and navigation device with a movable dial of the course and an arrow of a given direction.

The flight indicator contains:

- horizon indicator;

- roll scale with a roll index;

- movable pitch scale;

- a moving scale of barometric height with indication of a digital value, with an index of a given height and a digital value of a given height;

- the pressure of the day;

- a moving scale of instrument speed with indication of a digital value, with an index of a given speed and a digital value of a given speed;

- reference fixed index;

- director indexes.

The horizon is a rectangle consisting of two fields "Sky" and "Earth" of different colors. The conditional horizon line dividing them reflects the angular position of the aircraft: it rotates depending on the angle of heel and at the same time moves vertically depending on the pitch angle. Simultaneously with the rotation and movement of the horizon line, the ratio and position of the fields "Sky" and "Earth" change. At zero roll angle and pitch, the horizon line is horizontal in the middle of the rectangle, above it is the background "Sky", below it is the background "Earth". The pitch scale moves up and down in accordance with the value of the pitch angle of the aircraft along with the horizon line, which is the zero risk of the scale.

A plane symbol is displayed in the center of the horizon. It is a stylized image of the aircraft when viewed from the rear and consists of a central circle, two horizontal segments of a straight line and three vertical segments of a straight line, with one horizontal segment located to the left of the central circle at some distance from its edge, and the other horizontal segment is located to the right of the central circle at the same distance from its edge as the first horizontal segment, the first vertical segment is located above the central circle and touches it at the top , the second vertical segment adjoins with its upper end to the right end of that horizontal segment, which is located on the left, the third horizontal segment adjoins with its upper end to the left end of that horizontal segment, which is located on the right.

The airplane symbol is fixed, its center serves as a reference index for the pitch scale, and it is also the center around which the horizon turns and relative to which the horizon line moves.

The set path, set roll, and set speed are indicated using a single "Leader" pointer, this symbol is a symmetrical figure, similar in shape to the symbol of an airplane. It consists of four elements depicting various parts of the aircraft when viewed from the rear:

- the first part (fuselage) has the shape of a circle,

- the second part (wings) consists of two horizontal straight line segments adjacent to the left and right to the first part,

- the third part (keel) consists of a vertical line segment located above the center of the first part and touching the first part with one side thereof,

- the fourth part (chassis) is U-shaped and is located under the first part symmetrically with respect to the center of the first part.

The height director team is indicated by an index moving up and down along the height scale.

The main display elements are grouped near two conditional lines - horizontal and vertical.

- A horizontal line runs through the middle of the speed and altitude meters. In a steady horizontal flight along a given trajectory, all the main moving elements should be combined with this line:

- skyline;

- Director Index "Leader";

- director's height index;

- index of a given speed;

- index of a given height;

- arrow of vertical speed.

- The vertical line passes through the centers of two symbols depicting the aircraft itself: a reference horizon index and located in the center of the heading scale.

In the established ideal flight mode, all the main moving elements are combined with this line:

- roll index;

- pitch scale;

- Director Index "Leader";

- index of the track angle (a triangle on the outside of the course scale);

- arrow of a given direction (crosswise arrow);

- azimuth / course arrow from the VOR radio navigation system or from the radio compass (contour arrow).

The magnitude of the deviation of the moving element from these two lines serves as a measure of the deviation of the corresponding flight parameter from the established ideal regime.

Leader Index:

- moves relative to the center of the symbol of the aircraft left-right and up-down;

- turns around its center;

- varies in size.

Horizontally, the Leader pointer moves in accordance with the deviation from the given trajectory in the horizontal plane or the value of the director team at the heading, hereinafter referred to as ΔΨ.

The pointer moves vertically in accordance with the deviation from the given trajectory in the vertical plane or by the director command for pitch / angle of inclination of the trajectory, Δυ. For zero deviations ΔΨ and Δυ, the center of the Leader pointer falls into the center of the aircraft symbol.

The Leader pointer rotates around its center depending on the values of a given roll or roll director team, Δγ.

The geometric dimensions of the pointer vary depending on the deviation from the given speed Δν. When the speed is less than the specified one, the Leader symbol decreases in size - it is “deleted”, when the speed is greater than the specified one, it increases in size - it is “approaching”. When the speed is equal to the set, the symbol "Leader" has a nominal size, while it is combined with the symbol of the aircraft.

This depicts a “leader” flying in front of the aircraft, showing the required position and speed according to the “do as I do” principle.

When the aircraft is on the desired trajectory, flies with the required roll and at a given speed, the Leader pointer is combined with the aircraft symbol in both position and size. This intuitive display makes piloting easier.

The Leader Index contains four parts:

- the first is the central one, which serves to count the horizontal deviation;

- the second - horizontally oriented, serving to count the vertical deviation;

- the third - vertically oriented, serving to count the deviation from a given roll;

- fourth - serving to count the deviation from the set speed; its shape depends on the chosen shape of the airplane symbol.

The index may contain other parts that serve pictorial or other purposes.

In the preferred implementation of the Leader pointer in the form of an airplane, the first part is represented by a central circle, the second part is represented by horizontal segments on both sides of the circle (“wings”), the third part is shown by a vertical line above the circle (“keel”), the fourth part has the form of a bracket with downward directed and located under the center circle.

The visual attributes of each part are managed separately, depending on the reliability of the parameters that determine:

Δψ value for the first part;

Δυ value for the second part;

Δγ value for the third part;

Δν value for the fourth part.

Attributes can be the color of this part of the symbol, its blinking, the shape of the lines (solid, dotted, etc.), etc.

In a preferred implementation, this attribute is color. When the information in the paths Δψ, Δυ, Δγ, Δν is reliable, the four parts of the pointer have the same color, for example, blue or purple. If Δψ is unreliable, the first part of the pointer is indicated by a different color, for example, pale gray. Similarly, the color of the second part changes when Δυ is unreliable, the third part when Δγ is unreliable, and the fourth part when Δν is unreliable.

Thus, the pilot is given a warning that the corresponding movement or size of the Leader pointer at the moment does not reflect the actual deviation from the given parameter.

The source of information for the KPI are aircraft systems.

An inertial navigation system or heading vertical (ANN / HF) measures and displays the angles of roll γ, pitch υ and yaw ψ of the aircraft. The navigation computer (HB) contains in its memory a pre-entered flight path and provides data on the flight path (in the horizontal plane), which must be maintained. The system of air signals (SHS) measures and gives the speed V, the height H and the vertical speed V _y LA. From the control panel of the automatic flight control system (PU SAUP), the pilot sets the required height H _back and speed V _back . In director's control mode, the automatic flight control system (SAUP), based on information about the current flight parameters received from the ANN / KV, SVS systems, and the required trajectory in the horizontal and vertical planes received from the NV, PU SAUP systems, generates and issues control commands in the vertical plane δυ, the horizontal plane δψ and along the roll δγ. These commands take into account both the magnitude of the deviation and the dynamics of the aircraft. In other control modes of the aircraft, the SAUP system produces lateral deviations from the line of a given path ΔZ and deviations from a given height ΔH.

The flight-pilot indicator receives and displays the current flight parameters from the ANN / KV, SHS systems. According to information from the control panel of the control system for the control system for automated control system and the current speed from the SHS system, KPI calculates the deviation from the set speed Δν. This value, as well as the parameters received from the automatic flight control system SAUP and landing system (SP), are used in the KPI to control the pointer "Leader". In landing mode, the pointer moves horizontally in accordance with the deviation of the aircraft from the landing course Є _to , and vertically - in accordance with the deviation of the aircraft from the glide path of planning Є _g . When flying along a route in director mode, the pointer moves in accordance with the director teams in the vertical and horizontal planes δυ, δψ, at the same time it rotates in accordance with the director team for roll δγ. In manual control mode, the pointer moves horizontally in accordance with the value of the lateral deviation from the line of the given path ΔZ, and vertically - in accordance with the magnitude of the deviation from the given height ΔН.

The functional diagram of the flight indicator according to this invention contains an adder, multiplexers, blocks for calculating the characteristics of the Leader pointer, blocks for determining the accuracy of the input information, a screen and means for displaying symbols on this screen in accordance with the position and state of the aircraft — a symbol generator.

The parameters used to control the horizontal movement of the Leader pointer are sent to the multiplexer. Depending on the flight mode, the multiplexer selects one of these parameters - either the director team in the horizontal plane δψ, or the deviation of the aircraft from the landing course Є _to , or the lateral deviation from the line of the given path ΔZ.

Similarly, to control the vertical movement of the Leader pointer, the multiplexer selects either the director team in the vertical plane δυ, or the deviation of the aircraft from the glide path Є _g , or the deviation from the given height ΔH.

The selected values are sent from the multiplexers to the position calculation unit, which calculates the current position of the "Leader" pointer on the screen, i.e. its displacement relative to the aircraft symbol horizontally X and vertically Y, after which it passes the calculation results to the symbol generator.

The speed of the aircraft V and the target speed V _ass go to the adder, in which the difference between these two parameters is calculated - the deviation from the target speed Δ _V. The deviation value is sent to the size calculating unit, which, in accordance with this value, calculates the scale of indication of the Leader indicator m and transfers this scale to the symbol generator.

The director team for roll δγ enters the rotation calculation unit, which calculates the angle φ that the Leader pointer should be rotated (taking into account the direction of the mismatch). The calculated angle is transmitted to the symbol generator (HS).

The parameters used to control the "Leader" pointer are simultaneously transmitted to the blocks for determining the reliability of the parameters. Each block analyzes the value of the parameter and determines its reliability, using the redundancy of the transmitted information and a priori knowledge about the nature of the parameter change. For example, when transmitting a parameter with a serial code in accordance with GOST 18977-79 (the foreign counterpart is the ARINC 429 standard), the transmitted code contains additional bits that allow you to determine the state of the information source and the correct transmission.

Blocks for determining reliability form signs of reliability of the four parts of the pointer "Leader, which are transmitted to the symbol generator.

The symbol generator generates on the screen the image of the symbol of the aircraft, the moving pointer "Leader", scales, counters and other elements of the image format shown. For example, in the case of the implementation of an indicator based on a cathode ray tube (CRT), the laser beam using the deflecting system sets the path of the beam along the CRT screen, including the illumination of the phosphor at the desired points, so that the corresponding symbols are displayed on the screen. The Leader pointer is positioned by the symbol generator in accordance with the calculated coordinates X, Y, scaled in accordance with the calculated scale m and rotates through an angle φ. The image method of the parts of the pointer (color, etc.) is selected by the symbol generator depending on the signs of reliability of the parameters.

A disadvantage of the well-known flight indicator is that the angular and spatial position of the aircraft is determined by reading information from a large number of moving scales:

- the horizon, which is a rectangle consisting of two fields "Sky" and "Earth" of different colors. The conditional horizon line dividing them reflects the angular position of the aircraft: it rotates depending on the angle of heel and at the same time moves vertically depending on the pitch angle. Simultaneously with the rotation and movement of the horizon line, the ratio and position of the fields "Sky" and "Earth" change. At zero roll angle and pitch, the horizon line is horizontal in the middle of the rectangle, above it is the background "Sky", below it is the background "Earth". The pitch scale moves up and down in accordance with the value of the pitch angle of the aircraft along with the horizon line, which is the zero risk of the scale.

- roll scales with a roll index;

- movable pitch scale;

- a moving scale of barometric height with indication of a digital value, with an index of a given height and a digital value of a given height;

- a moving scale of instrument speed with indication of a digital value, with an index of a given speed and a digital value of a given speed;

- reference fixed index;

Such a large number of movable linear scales for indicating pitch, speed and pitch angle, a dial for indicating roll, indices of a given speed and height clutter the display field of the flight control indicator and reduce the informational visibility of the current flight parameters and dissipate the pilot’s attention since to estimate the quantitative value of the listed parameters, it is required to sequentially read information from the corresponding scales, which leads to an increase in the time of the spatial position estimation And the instruments and a reduction in time to evaluate the spatial position of the aircraft and making the correct control action, which does not exclude emergency and catastrophic flight of consequences associated with the loss of pilot spatial orientation in the management of the aircraft in extreme flight conditions.

The loss of spatial orientation by the pilot when controlling the aircraft in extreme flight conditions with a lack of time and attention will occur in manual and automatic flight control modes of the aircraft due to the fact that the control signals for the spatial deviation between the current flight path and a given flight path (ΔZ, ΔH) and the angular position signals for angular deviations of the course angle and pitch angle (δυ, δΨ), as well as control signals to the aircraft during landing deviation from course _to Je and landing aircraft deviations from the glide path Planning Yea _r only intended for the rolling index "Leader" with a fixed index "Airplane".

The immobility of the “Plane” index on the display field of the flight-pilot indicator creates a condition under which the pilot does not see the angular position of his own aircraft in space, but presents it through the movable index “Leader”, which leads to a loss of spatial orientation and a decrease in flight safety.

The technical task of the claimed invention is to increase safety by creating on the display field of the screen a flight-pilot indicator of a simultaneous uniform figurative complexity of the current information for the roll-pitch-height-glide pilot, which in a reliable and understandable form would show the pilot in a single moment of time:

- the angular position of the aircraft controlled by it in space (roll, pitch, height, glide angle) with the aerodynamic and inertial-mass characteristics of its real aircraft;

- deviations from the parameters of the specified flight path of the aircraft in space (height, lateral deviation);

- a figurative representation of the calculated parameters, correcting deviations from a given trajectory (roll, pitch, glide angle, speed);

- a figurative representation of radio altitude on the scale of a fixed uneven scale of the flight altitude.

The technical problem is ensured by the fact that in the flight control indicator containing a screen on which a reference index in the form of a stylized image of the plane when viewed from the rear with the landing gear (“Airplane”) indicating the current position of the aircraft in space is displayed, which is fixed relative to the center of the display field of the screen, the movable index displayed on the screen in the form of a stylized image of the aircraft when viewed from the rear with the landing gear extended, indicating the desired position of the aircraft in space ("Leader"), with the ability to orot around its center of symmetry, as well as moving vertically and horizontally relative to the Airplane index, a symbol generator connected to the screen, controls for the Leader moving index, made in the form of blocks for calculating the Leader characteristics, the inputs of which receive signals from aircraft systems, and from the outputs of which signals are sent to the symbol generator in accordance with the height control error value, which ensure the movement of the Leader index along the indicator field in the vertical direction, along the pitch angle and turning it around the center of symmetry in accordance with the error in roll angle, increasing or decreasing the linear dimensions of the Leader index with increasing or decreasing the set flight speed, respectively, so that at zero error values for all the controlled parameters, the Leader index is combined with the “Airplane” index, the “Airplane” index is made to rotate around its center of symmetry, and the stylized image of the “Airplane” and “Leader” indices is made in the form of one horizontal line, symbol flying wings, and one vertical line, symbolizing the keel of the aircraft and intersecting the horizontal line in its center at a right angle, and is additionally equipped with a unit for calculating the parameters of the current glide angle, a unit for calculating the estimated angle of heel, a unit for calculating the estimated glide angle, and a unit for calculating the deviation of the aircraft the flight altitude and the scale factor of the deviation of the flight altitude of the aircraft, the unit for calculating the value of the calculated pitch angle, the unit for calculating the lateral deviation and the scale factor of the side of aircraft landing, the inputs of which receive signals from the aircraft systems, and the outputs of which are connected to the inputs of the symbol generator, and is also configured to indicate the radio altitude index and a fixed uneven scale of the flight altitude value displayed on the vertical side of the boundary of the display field of the screen with a zero value height, located at the level of a horizontal line passing through the center of the display display field, while both the index “Aircraft” and “Leader” are configured to simultaneously display the current the glide angle and pitch angle of the Airplane index and deviations from the given glide angle and pitch angle of the Leader index by indicating a triangle whose base is equal to the length of the horizontal straight line symbolizing the aircraft’s wings, and the position of the triangle apex corresponds to the current value of the pitch angle and index slip angle "Aircraft" and deviation from a given value of the pitch angle and the slip angle of the "Leader" index.

The invention is illustrated by drawings.

Figure 1 shows the front of the device flight indicator, displaying information about the flight of the aircraft.

Figure 2 - Fragment of the flight of the aircraft on the display field of the screen, which shows a stylized shape of the index "Leader", index "Airplane" at zero angles of roll, pitch and slip.

Figure 3 shows a diagram of the pairing of aircraft systems with a flight indicator.

Figure 4 shows a functional diagram of a flight indicator.

Figure 5 - Fragment of the flight of the aircraft on the display field of the screen, when the indices "Leader" and "Airplane" depict a positive pitch angle at a zero angle of slip and a zero angle of heel.

Figure 6 - Fragment of the flight of the aircraft on the display field of the screen, when the indices "Leader" and "Airplane" depict a negative pitch angle at zero slip angle and zero roll angle.

Figure 7 - Fragment of the flight of the aircraft on the display field of the screen, when the indices "Leader" and "Airplane" depict left sliding at zero pitch angle and zero roll angle.

On Fig - Fragment of the flight of the aircraft on the display field of the screen, when the indices "Leader" and "Airplane" depict the right glide at zero pitch angle and zero roll angle.

Figure 9 - Fragment of the flight of the aircraft on the display field of the screen, when the indices "Leader" and "Airplane" depict simultaneously a positive pitch angle and left slip at a zero roll angle.

Figure 10 - Fragment of the flight of the aircraft on the display field of the screen, when the indices "Leader" and "Airplane" depict simultaneously a positive pitch angle and right glide at zero roll angle.

Figure 11 - Fragment of the flight of the aircraft on the display field of the screen, when the indices "Leader" and "Airplane" simultaneously depict a negative pitch angle and right glide at zero roll angle.

On Fig - Fragment of the flight of the aircraft on the display field of the screen, when the indices "Leader" and "Airplane" simultaneously depict a negative pitch angle and left slip at a zero roll angle.

On Fig - Fragment of the flight of the aircraft on the display field of the screen, when at the same time the positive pitch angle, left slip and positive roll angle for the index "Airplane" and the negative pitch angle, right slip and negative roll angle for the index "Leader".

On Fig - Fragment of the flight of the aircraft on the display field of the screen depicting the current angular position of the indices "Leader" and "Airplane" at the time of the deviation of the aircraft from a given flight path.

On Fig - Fragment of the flight of the aircraft on the display field of the screen, when the current value of the speed vector of the aircraft Vtek is less than the programmed vector of the speed of the aircraft Vset. Index "Leader" is reduced in size - "deleted."

In Fig.16 - Fragment of the flight of the aircraft on the display field of the screen when the current value of the speed vector of the aircraft Vtek is more than the programmed vector of the speed of the aircraft V back. The Leader index is increasing in size - it is approaching.

On Fig - Fragment of the flight of the aircraft on the display field of the screen, when the current value of the speed vector of the aircraft Vtek equal to the programmed set of the speed vector of the aircraft V back. The Leader index has a geometric size equal to the geometric size of the Airplane index.

On Fig - Fragment of the flight of the aircraft in the display field of the screen, when the flight speed of the aircraft is greater than the programmed flight speed, there is a negative deviation in the lateral direction and an excess of flight altitude with a positive roll angle, a positive pitch angle and left slip.

On Fig - Fragment of the flight of the aircraft on the display field of the screen, when the flight speed of the aircraft is close to the programmed flight speed with a positive deviation in the angle of heel, without deviating the flight path in height and in the lateral direction.

On Fig - Fragment of the flight of the aircraft on the display field of the screen, when the flight speed of the aircraft is less than the programmed flight speed, the flight path is lower than the programmed one, there are no deviations in the angle of heel and the angle of slip. The requirement of the Leader index is to increase the pitch angle.

In Fig.21 is a fragment of the landing of the aircraft, when the current flight speed, flight altitude, roll angle, pitch angle, the angle of glide of the aircraft are close to the programmed values. The automatic flight control system tells the pilot that when landing according to the flight program at the moment it is necessary to execute the command "release the landing gear".

The flight indicator (figure 1) consists of:

- the screen of the flight indicator 1, then screen 1;

- navigation field 2 of screen 1;

- indication field 3 of screen 1;

- displayed on the display field 3 of the screen 1 of the movable index, not controlled by the pilot "Leader" 4, then "Leader" 4 (Fig. 1), made in the form of a stylized image of the aircraft when viewed from the rear, visualizing the deviation of the aircraft relative to the specified parameters of the programmed flight path having the ability to rotate around its center of symmetry and freely moving vertically and horizontally relative to the center of the display field 3 of the screen 1;

- displayed on the display field 3 of the screen 1 of the movable index controlled by the pilot "Airplane" 5, then "Airplane" 5 (Fig. 1), made in the form of a stylized image of the aircraft when viewed from the rear, visualizing the current angular position of the aircraft and the dynamics of its change in a space having the ability to rotate around its center of symmetry, located in the center of the display field 3 of the screen 1;

- "Leader" 4 and "Airplane" 5 represent (figure 2) a stylized shape of the aircraft when viewed from the rear, which is represented by one horizontal line symbolizing the wings of the aircraft, and one vertical line symbolizing the keel of the aircraft, and the vertical line intersects the horizontal line in its center at right angles. "Leader" 4 and "Airplane" 5 (figure 2) have an identical shape and the lines forming the indices "Leader" 4 and "Airplane" 5 are made with different thickness and brightness;

- indicated on the display field 3 of screen 1 of the radio altitude index 6 (Fig. 1), representing its real value presented on a scale and made in the form of a horizontal line that moves in the display field 3 of screen 1 vertically from the center of symmetry of the "Airplane" 5 to the bottom of the display field 3 of screen 1;

- displayed on the display field 3 of the screen 1 fixed uneven located on the vertical side of the border of the display field 3 of the screen 1 scale aircraft altitude 7 flight of the aircraft (Fig. 1), then a scale of altitude 7 with zero aircraft altitude, located at the level of a horizontal line passing through the center of the display field 3 of screen 1;

- displayed on the navigation field 2 of the screen 1 of various navigation information of the current values of the flight parameters of 8 aircraft, in particular the image of the vertical speed scale of the aircraft, a planning and navigation device with a movable circular heading scale and an arrow of a given direction (figure 1).

To visualize flight information (figure 3), the flight pilot indicator KPI 9 receives and processes data from the automatic flight control system SAUP 10, which receives flight parameters from the main aircraft systems:

- SVS 11 airborne signal systems - parameters about the current value of the flight altitude of the aircraft Ntek, about the current value of the aircraft velocity vector Vtek and the current projection of the vertical speed vector of the aircraft Vyg tech;

- inertial navigation system (ANN) 12 - parameters about the angular and spatial position of the aircraft: υtek, γtek, φtek, respectively, the current value of the pitch angle, the current value of the angle of heel, the current value of the yaw angle and Хtek - the current value of the flight range of the aircraft, Ztek - current lateral deviation of the aircraft;

- navigation calculator of initial data (НВ ИД) 13 - parameters of the three-dimensional programmed flight path in the earth coordinate system: flight time on the route - T, distance on the route from the start point - X back, flight altitude on the route - H back, lateral deviation - Z back, programmatically the aircraft’s set flight altitude to execute the “remove landing gear” command and the “lower landing gear” command - H landing gears are directly sent to the automatic flight control system (SAUP) 10 and to the navigation computer for calculating data (NV RD) 14, in which they are converted to Relatively set aircraft flight parameters:

- in the Earth's coordinate system (ZSC):

Vxg ass - projection of speed on the Xg axis;

Vyg ass - projection of speed on the Yg axis;

Vzg ass - projection of speed on the Zg axis;

Θzad - the angle of inclination of the aircraft trajectory;

Ψzad - angle of rotation of the aircraft trajectory;

N-chassis - programmed flight altitude of the aircraft for the execution of the "remove landing gear" command and the "release landing gear" command.

- in a linked coordinate system:

γset - roll angle,

υset - pitch angle,

φset - yaw angle.

- navigation computer calculating data (NV RD) 14, from which additionally set flight parameters of the aircraft enter the automatic flight control system (SAUP) 10.

All the information necessary for the pilot to control the flight of the aircraft from the automatic flight control system (SAUP) 10 enters the flight control indicator 9.

The composition of the KPI 9 (Fig. 4) includes a symbol generator (HS) 15, which generates commands for displaying the current flight parameters of the aircraft by signals coming from:

- a unit for calculating the parameters of the current sliding angle 16;

- unit for calculating the value of the estimated angle of heel 17;

- a unit for calculating the estimated slip angle 18;

- block calculating the coefficient of flight speed LA 19;

- a unit for calculating aircraft deviation in flight altitude and a scale factor for deviation of aircraft altitude in flight 20;

- a unit for calculating a value of a calculated pitch angle 21;

- a unit for calculating the lateral deviation and the scale factor of the lateral deviation of the aircraft 22.

All display commands created in the character generator (HS) 15 are displayed on screen 1 of KPI 9, from which the pilot reads the necessary information.

The symbol generator (GS) display commands 15 indicate: “Leader” 4, “Airplane” 5, “radio height” index 6, fixed uneven scale of height value 7, the command “remove the chassis” and the command “release the chassis” and various navigation information of the current values flight parameters of 8 aircraft.

To visualize the "Leader" 4 (figure 4) on the display field 3 of the screen 1 in the symbol generator (HS) 15 receives signals:

from the unit for calculating the value of the estimated angle of heel 17 receives the value of the estimated angle of heel γcalc;

from the unit for calculating the estimated sliding angle 18, the value of the calculated sliding angle βcalc;

from the unit for calculating the coefficient of flight speed LA 19 receives the value of the coefficient of the scale of the speed of flight LA mV;

from the unit for calculating the deviation of the aircraft by flight altitude and the scale factor of the deviation of the flight altitude of the aircraft 20, the value of the scale factor of the deviation of the flight altitude of the aircraft mH;

from the unit for calculating the value of the estimated pitch angle 21, the value of the calculated pitch angle υ calc;

from the unit for calculating the lateral deviation and the scale factor of the lateral deviation of the aircraft 22 receives the value of the coefficient of scale of the lateral deviation of the aircraft mZ.

To visualize “Airplane” 5 on the display field 3 of screen 1, the character generator (GS) 15 receives from the block for calculating the parameters of the current sliding angle 16 (Fig. 3): the current value of the sliding angle βtek, the current values of the pitch angle υtek and the current value of the angle of heel γtec.

To visualize the "radio altitude" index 6 on the display field 3 of the screen 1, the symbol value (GS) 15 from the block for calculating the aircraft deviation in flight altitude and the scale factor for deviation in flight altitude of the aircraft 20 receives (Fig. 3) the current value of the aircraft flight height NTec.

To visualize the command “remove the landing gear" and the command "release the landing gear" for the Leader index 4 on the display field 3 of screen 1 in the symbol generator (HS) 15 from the aircraft altitude deviation calculation unit and the aircraft altitude deviation scale factor 20 arrives ( figure 4) a difference signal of the current value of the flight altitude of the aircraft Ntek and programmable flight altitude of the aircraft H back = H chassis to execute the command "remove the chassis" and the command "release the landing gear".

To visualize a fixed non-uniform scale of the aircraft flight altitude 7 value located on the vertical side of the border of the display field 3 of screen 1, the procedures of the specialized programming language are used in the symbol generator (HS) 15, which are not the subject of the invention and are not considered in this case.

In the proposed flight-pilot indicator, a separate representation of blocks such as: adder, multiplexer,

- blocks for calculating the characteristics of the moving indices "Leader" 4 and "Airplane" 5;

- blocks for determining the reliability of input information;

- means of displaying on the screen the symbols of the figures in accordance with the position and condition of the aircraft;

- devices and other elements that perform the reception and processing of flight and navigation information used to control figures, symbols, moving scales, pointers and other elements of the image format in figure 3 are not shown.

To ensure the operation of the flight-pilot indicator, initial information is needed from the block of the automatic flight control system (SAUP) 10 (Fig. 3) of the aircraft, which receives data on the dynamic and trajectory flight parameters from the air signal system (AAS) 11, inertial navigation system ( ANN) 12, the navigation calculator of the source data (NV ID) 13 and the navigation calculator of the calculated data (NV RD) 14.

Measuring the current trajectory and current angular flight parameters of the aircraft, the inertial navigation system (ANS) 12 outputs to the automatic flight control system (SAUP) 10: the current value of the roll angle is γtek, the current value of the pitch angle is υtek, the current value of the yaw angle is φtec, the current range value - Xtek, current lateral deviation - Ztek.

The block of the automatic flight control system (SAUP) of 10 aircraft also receives data from navigation computers, which transmit the parameters of the reference flight path and calculate additional navigation parameters to provide the programmed flight path of the aircraft. Aircraft navigation calculators contain not only the data of the flight path parameters, but also include the aerodynamic characteristics of the aircraft, inertial-mass, weight and other parameters, which depend on flight safety and the key to the fulfillment of the task. These data are important, but do not relate to the subject of the invention and therefore are not considered in the claimed proposal. For the claimed invention, when visualizing the indices "Leader" 4 and "Airplane" 5, the trajectory parameters are important, because they create a figurative mutual spatial and angular position of the indices on the KPI screen, identical to the real aircraft and the virtual leader with the aerodynamic and inertial-mass characteristics of the real aircraft.

The parameters of the reference flight path of the aircraft are entered into the program of the navigation calculator of the initial data (NV ID) 13 in the form of numerical values of the parameters of the nodal points of the programmed flight path of the aircraft in the earth's coordinate system: T is the flight time on the route, Xset is the distance on the route from the starting point, H-back — flight altitude on the route, Z-back — lateral deviation on the route, H-chassis — programmable aircraft altitude for the execution of the “remove landing gear” command and the “lower landing gear” command.

The programmed parameters of the flight path of the aircraft are algorithmically processed in the navigation calculator of the initial data (NV ID) 13 and transmitted to the block of the navigation calculator of the calculated data (NV RD) 14, where they are converted into additional parameters of the flight of the aircraft: - for the Earth coordinate system (GSC): Vxg rear - projection of speed on the Xg axis, Vyg rear - projection of speed on the Yg axis, Vzg rear - projection of speed on the Zg axis, ад back - angle of inclination of the aircraft trajectory, ад rear - angle of rotation of the aircraft trajectory and for the associated coordinate system (SSC): γ rear - roll angle a, υset - pitch angle, φset - yaw angle.

Together, the parameters of the reference flight path of the aircraft and the calculated additionally specified flight parameters of the aircraft represent a set of data of the software-defined flight path of the aircraft as a function of time, which makes it possible to withstand not only spatial, but also angular parameters of the aircraft in flight.

In contrast to the prototype, in which the flight path is divided into a horizontal section and a landing path, the programmed flight indicator uses the programmed flight path of the aircraft as a function of time in a three-dimensional Cartesian earth coordinate system for the functioning of the claimed pilot flight indicator.

The data set of the programmed flight path of the aircraft in function of time comes from the unit of the navigation calculator of the source data (NV ID) 13 and the block of the navigation calculator of the calculated data (NV RD) 14 in the automatic flight control system (SAUP) 10, in which the upcoming trajectory is finally calculated flight of the aircraft in the form of specified parameters.

In addition to the data set of the programmed flight path of the aircraft, to ensure the operation of the flight-pilot indicator, the current values of the flight path parameters of the aircraft, which are measured by the airborne signal system (SHS) 11, are required, forming a data set: about the current value of the flight altitude of the aircraft - Htek, about the current value of the vector speed of the aircraft - Vtek and the current projection of the vector of vertical speed of the aircraft - Vyg, which are currently issued to the automatic flight control system (SAUP) 10 to ensure the operation of the function algorithms p znostnyh values programmatically set parameters and current aircraft flight parameters.

The main one on board the aircraft is the pilot, for whom the flight indicator provides an indication of reliable safe flight and optimal performance of the assigned task, therefore commands are received from the pilot analyzing the flight by visual presentation on the display field 3 of screen 1 to the automatic flight control system (SAUP) 10 pilot-flight indicator KPI 9. Depending on the visual representation of the flight situation presented on the display field 3 of screen 1, the pilot, controlling the aircraft, selects either Mode flight director control dependent or mode with disabled director control addiction. Choosing a director's dependence of the regime, the pilot uses either automatic flight control, i.e. the function of the pilot-operator, or uses the manual flight control mode. Choosing a flight mode with the director dependent off, the pilot controls the flight in manual free flight control mode and transmits the selected control mode command for execution to the automatic flight control system (SAUP) 10.

From the automatic flight control system (SAUP) 10, the output data of the current flight path parameters and the specified flight path parameters of the aircraft, related to the spatial, speed, angular parameters of the aircraft for the mobile indexes "Leader" 4 and "Airplane" 5, data on "radio height" 6 , the “remove landing gear” command, the “lower landing gear” command, and the data for “visualizing navigation instruments” are transmitted to the flight control indicator KPI 9 to function blocks 16 ÷ 22, in which visualizing signals for a symbol generator (GS) are generated 15 (FIG. 4), in which the flight situation along the flight route is formed and transmitted to the display field 3 of screen 1.

In the pilot-flight indicator KPI 9, the internal programming language forms an image of a fixed uneven scale for the flight altitude 7 value of the aircraft, which is also transmitted to the display field 3 of screen 1. A fixed uneven scale for the altitude 7 of the aircraft flight is located on the vertical side of the boundary of the display field 3 of screen 1.

The fixed uneven scale of the aircraft flight altitude 7 allows the pilot of any skill not to be distracted by the displayed value of the current flight altitude if it (altitude) is higher than the maximum value of the aircraft altitude 7 indicated on the fixed uneven scale proposed in the invention. At values of the current flight altitude of the aircraft close to the maximum value of a fixed uneven scale of altitude 7 of the flight of the aircraft, moving the "radio height" index 6 on the display field 3 of screen 1 is almost imperceptible and does not distract the pilot's attention from the mission assigned to him.

With the current flight altitude of the aircraft, when the pilot needs to be especially careful (pre-landing modes or flying at low altitudes), the speed of movement of the "radio height" index 6 on the display field 3 of screen 1 increases in accordance with the step of marking the uneven scale of the flight altitude. Moving the index "radio height" 6 on the display field 3 of screen 1 attracts the attention of the pilot to perform maneuvers associated with a change in height. The speed of movement of the index "radio height" 6 on the display field 3 of the screen 1 increases if the flight altitude decreases. The lower the aircraft’s flight altitude, the faster the radio altitude index 6 moves to the center of the display field 3 of screen 1, attracting the attention of the pilot with a changing picture of the display field 3 of screen 1. The parameter of the rapidly changing flight height draws the pilot’s attention to this particular flight path factor and formally warns its readiness for actions caused by the current flight altitude, up to the planned instrument or emergency landing. The pilot will always pay attention to the movement of the "radio altitude" index 6, which will provide him with reliable and safe flight without stress in any extreme flight conditions with a shortage of time and attention.

For the pilot, the angular position of his aircraft on the display field 3 of screen 1 is identified by the angular position of the "Airplane" 5 index by the parameters of the angular position of the aircraft at a given time: the current glide angle is βtek, the current value of the pitch angle is υtek and the current value of the angle of heel is γtek.

The current glide angle βtec is calculated by the procedure using the output data of the angular current parameters of the flight path of the aircraft (Fig. 4) coming from the automatic flight control system (SAUP) 10: υtek is the current value of the pitch angle, γtec is the current value of the angle of roll, φtec is the current yaw angle value, Ψ tech is the value of the angle of rotation of the aircraft trajectory, Θ tech is the value of the current angle of inclination of the aircraft trajectory, which are transmitted to the block for calculating the parameters of the current sliding angle 16, where the output of the angular current parameters the trajectory of aircraft flight and output the velocity vector data for the current angular position are converted into the transition matrix from "related coordinate system to the earth coordinate system," and from the "earth coordinate system to the coordinate system speed", respectively. The matrix multiplication procedure yields a new matrix with elements of the angle of attack and glide angle on the flight path of the aircraft at the current time. At the output of the unit for calculating the current glide angle 16, the current roll angle is γtek, the current pitch angle is υtek and the current glide angle is βtek as visualizing signals for the Airplane index 5 on display field 3 of screen 1.

The Leader index 4 is displayed on the display field 3 of screen 1 for the current time, the estimated roll angle is γcalc, the calculated value of the pitch angle is υcalc and the calculated value of the slip angle is βcalc.

Unlike the prototype, the roll angle of the Leader index 4 is calculated as the sum of the current roll angle of the aircraft controlled by the pilot — γ tech, the programmed roll angle of the aircraft along the flight route — γ rear and the correction angle of the roll angle — γ pp, which depends on the lateral deviation LA from a given flight path.

For this, the unit for calculating the value of the estimated angle of heel 17 from the automatic flight control system (CAM) 10 receives: γtek - the current value of the heel angle, Ztec - the current lateral deviation, γset - the set value of the angle of heel, Zset - the lateral deviation of the specified coordinate in the flight program LA The value of the calculated lateral deviation of the aircraft trajectory ΔZ = (Ztek-Zzad) enters the function of calculating the correction value of the roll angle γppr. The sum of the current value of the angle of heel γtek, the given angle of heel γset and the correction value of the angle of heel γppr is the value of the estimated angle of heel γcalc = (γtec + γset + γppr), which is transmitted to the symbol generator (HS) 15 (figure 4) as a visualizing signal to the mobile uncontrolled pilot index "Leader" 4 in the display field 3 of screen 1.

Visualized for the Leader index 4, the calculated value of the glide angle — βcalc — comes from the block for calculating the estimated glide angle 18, to which the input of the programmed angular position of the aircraft on the trajectory comes from the automatic flight control system (SAUP) 10: γset — angle of heel, υset - pitch angle, φset - yaw angle and input data of programmed values of the angles of the spatial position of the aircraft velocity vector, Ψset - angle of rotation of the aircraft trajectory and Θset - angle of inclination of the aircraft trajectory. Received input data are converted into transition matrices from the “associated specified coordinate system software to the Earth coordinate system” and from the “earth coordinate system to the high-speed specified program coordinate system”, respectively. As a result of the matrix multiplication procedure, we obtain a new matrix with calculated elements of programmed angles of attack and glide angles on the flight path of the aircraft for a given point in time. The value βcalc - the value of the calculated sliding angle, set by software, we use as a visualizing signal for the index "Leader" 4 in the display field 3 of screen 1.

To take into account the influence of the current flight speed of the aircraft, the output Vset is the programmed value of the aircraft speed vector and Vtek is the current value of the aircraft speed vector from (Fig. 4) of the automatic flight control system (SAUP) 10, we feed it to the aircraft flight speed scale factor calculation unit 19, where the output values are compared. The deviation of the current flight speed of the aircraft from the given flight speed ΔV = (V-V-Vtek) is scaled and, as the visualizing signal of the scale factor of the flight speed of the aircraft mV, is fed to the symbol generator (GS) 15 to indicate an increase or decrease in the similarity of the geometric size of the figure of the Leader index " four.

For visualization on the display field 3 of screen 1, the aircraft deviation in height from the programmed flight path is fed to the Leader index 4 height deviation proportional to the coefficient of deviation in flight altitude deviation mH mH, which is calculated in the unit for calculating aircraft deviation in flight altitude and coefficient the scale of the deviation of the flight altitude of the aircraft 20 according to the output data Hset — the programmed flight altitude of the aircraft on the route and Htec — the current value of the aircraft flight altitude (Fig. 4) received from the automatic flight control system (ACS) P) 10. The aircraft flight altitude set by the program on the route and the current aircraft altitude are compared. The aircraft deviation along the flight altitude trajectory ΔH = (H-H-Htek) is scaled to the parameter of the aircraft altitude deviation scale factor mH and, as the control signal of the deviation scale factor mH, is transmitted to the symbol generator (HS) 15 to generate the spatial position on the display field 3 of screen 1 large-scale deviations of the Leader index 4 relative to the center of the display field 3 of the screen 1, in which the Airplane index 5 is located (Fig. 14).

The deviation of the aircraft on the trajectory along the flight altitude ΔH = (Had-Htek) is compensated by the parameter of the calculated pitch angle υcalc, which is one of the factors of the deviations that arise. In order to obtain the calculated pitch angle from the automatic flight control system (SAUP) 10, the values of vadd - the given pitch angle, Hread - with the programmed flight altitude on the route, υtek - the current aircraft pitch angle, Htec - the current aircraft flight height, are fed to the input of the calculation unit the value of the calculated pitch angle 21, in which the calculated deviation of the aircraft in flight altitude ΔH = (Htek-H back) is fed to the processing function to calculate the correction value of the pitch angle υпр. The sum of the current value of the pitch angle υtek, the specified pitch angle υspr and the correction value of the pitch angle υppr - is the value of the calculated pitch angle υcc = (υтек + υsp + υppr), which is transmitted to the symbol generator (GS) 15 (Fig. 4) and from which as a visualizing signal, it comes to the mobile index “Leader” 4, which is not controlled by the pilot.

The visualized figure of the Leader index 4 for the current time instant fully represents the programmed angular position on the flight path of the aircraft in the display field 3 of the screen 1 according to the parameters of the calculated angles: the calculated value of the roll angle is γcalc, the calculated value of the pitch angle is υcalc and the calculated value slip angle - β calc.

Visualization on the display field 3 of the screen 1 of the aircraft deviation in the lateral direction from the programmed flight path complements the indicative picture of the aircraft spatial deviation, angular deviation and speed deviation on the route trajectory. The pilot sees reliable information about deviations from the given parameters of the flight path and at any time performs a safe maneuver to correct the situation, which provides the pilot with confidence, reliability and safety in flight even in extreme conditions with a shortage of time and attention.

To calculate the deviation of the aircraft in the lateral direction from the programmed flight path, the output data of the automatic flight control system (SAUP) 10 (Fig. 4) Zset - lateral deviation of the programmed flight coordinates of the aircraft and Ztec - the current lateral deviation of the flight path of the aircraft is fed to the calculation unit the lateral deviation and the scale factor of the lateral deviation of the aircraft 22, in which the values of the output data are compared. The lateral deviation of the aircraft trajectory ΔZ = (Zad-Ztek) is scaled to the value of the coefficient of scale of the lateral deviation of the aircraft mZ. As a control signal, the coefficient of deviation scale mZ is transmitted to the symbol generator (HS) 15 to generate the position of the scale deviation of the Leader index 4, visualizing the scale ΔZ of the lateral deviation of the aircraft trajectory relative to the center of the display field 3 of screen 1, in which the Airplane index 5 is located (Fig. 14).

The proposed flight-control indicator, while maintaining the reliability and safety of flight in accordance with the proposed scheme for interfacing aircraft systems with the flight-flight indicator (Fig. 3) and the functional diagram of the flight-flight indicator (Fig. 4), allows you to execute reminder commands about or flight procedures. For example: after take-off at a height greater than H chassis, execute the "remove chassis" command, and before landing at a height lower than H chassis, execute the "release chassis" command. For this, the output parameter of the automatic flight control system (SAUP) 10, obtained from the navigation source data calculator (НВ ИД) 13 in the form of an aircraft flight path with a value of H landing - the maximum flight altitude of the aircraft with landing gear, at which the pilot is reminded that on take-off under the condition (Нtek> Нshassis), it is necessary to execute the "remove the chassis" command, on the landing trajectory, under the condition (Нtek <Нshassis), the command "release the chassis" must be executed. H chassis - the maximum flight altitude of the aircraft with the landing gear and received from the airborne signal system (CBC) 11 Htek - the current value of the flight altitude of the aircraft is compared and when the current flight altitude of the aircraft on the landing path NT will be less than the programmed flight altitude of the aircraft on the path with the landing gear H chassis, visualizing the "release the chassis" command is sent from the character generator (HS) 15 to the display field 3 of screen 1 to the Leader index 4. The "release the chassis" command is displayed in the form of two lines that appear under horizontal iyami symbolizing wings stylized LA index "Leader" 4.

The pilot, observing the Leader index 4 on the display field 3 of the screen 1 with the visualized reminder command “remove the landing gear” on take-off and “lower the landing gear” before landing, will always be insured against flying with the landing gear landing and will never land the aircraft with emergency consequences without chassis released.

Indicated on the display field 3 of the screen 1 command reminder index "Leader" 4 on the position of the chassis on the flight path of the aircraft is worked out by the pilot from the cockpit by turning on the toggle switch with the position "release the chassis" or "remove the chassis." The command selected by the pilot is transmitted to the automatic flight control system (SAUP) 10, then to the flight control indicator 9 and to the character generator (GS) 15 to the “Airplane” 5 index, thereby visualizing the landing gear control command selected by the pilot.

Presented on the display field 3 of screen 1, the index of the figurative "radio height" 6 is the converted current value of the aircraft flight altitude NTek, which in the character generator (GS) 15 KPI as a visualizing signal in the scale of its real value is represented as a horizontal straight line that moves along vertically up and down on the display field 3 of screen 1 from the “Plane” 5 index to the bottom of the display field 3 of screen 1, in accordance with the value of the fixed uneven scale of the aircraft flight altitude located at the vertical side of the border of the display field 3 of screen 1, and the zero value of the scale is located at the level of the horizontal line passing through the point of center of symmetry of the index "Airplane". The combination of a visual representation of the imaginary "radio height" 6 and a fixed uneven scale of the aircraft flight altitude does not distract the attention of the pilot from the fulfillment of the flight task and at the same time ensures the reliability and safety of the flight without stress.

A fixed uneven scale of the aircraft flight altitude value is formed by the standard internal programming language of the symbol generator (GS) 15 KPI (Fig. 4) and is displayed on the boundary of the display field 3 of screen 1, and the zero value of the scale is located at the level of the horizontal line passing through the point of symmetry of the index "Aircraft" 5. A fixed uneven scale for the altitude 7 of an aircraft flight is presented in (Figs. 1, 2) and (Figs. 5-21).

From the output parameters of the automatic flight control system (SAUP) 10 in the symbol generator (HS) 15, visualizing signals are generated for displaying on the navigation field 2 of screen 1 of the presentation of navigation devices reflecting the parameters of the current flight path of the aircraft.

The visualization signals on the display field 3 of screen 1 indicate the full spatial and angular position of the pilot-controlled aircraft through visualizing signals to form indices: - "Leader" 4, - "Airplane" 5, - "Radio height" 6, - index of a fixed uneven scale 7 the flight altitude value of the aircraft located on the border of the display field 3 of screen 1 and the presentation of the values: calculated pitch angle - υ calc, current pitch angle - υtek, estimated roll angle - γcalc, current roll angle - γtec, current angle value is slipped ia - βtec, the values of the estimated slip angle - βcalc, the current value of the aircraft flight altitude according to the radio altimeter - Ntec.

The selected stylized form of the aircraft from the rear, in the form of two mutually perpendicular lines, implies for the Leader 4 and Airplane 5 indices two mutually perpendicular reference scales for the pitch and glide angles, the zero mark of which is located in the center of the horizontal line. There is no graduation of scales, since the pilot does not need to peer into the values of the indicated angles due to the fact that the exact angular position of the aircraft identified by the Airplane index 5 is determined by the angular position of the displayed Leader index 4. The selected stylized form of the aircraft from the rear, in the form of two mutually perpendicular lines, implies for the Leader 4 and Airplane 5 indices, the function of the mobile coordinate system is “pitch angle - glide angle”, in which negative values of the skew angle are located along the abscissa along the straight line symbolizing the aircraft’s right wing the surface of the aircraft along the straight line, symbolizing the left wing of the aircraft, there are positive values of the glide angle, along the ordinate axis, along the line symbolizing the keel of the aircraft, positive values of the pitch angle are located, and along the line symbolizing the continuation of the keel of the aircraft, negative values of the angle are located pitch. The center of the horizontal straight line symbolizing the wings of the aircraft is the point of the center of symmetry, relative to which the Leader 4 and Airplane 5 indexes rotate, visualizing the estimated bank angle - γcalc and the current bank angle - γtec, respectively. The point of center of symmetry of the index "Airplane" 5 is fixed and is located in the center of the display field 3 of the screen 1.

The point of center of symmetry of the Leader index 4 moves along the entire display field 3 of screen 1, depending on the visualization signals generated in the symbol generator (HS) 15 of the KPI 9. The rotation of the Airplane index 5 relative to the point of the center of symmetry visually represents the sign and magnitude of the current angle pilot-controlled aircraft roll - γtec. The current positive roll angle for the “Aircraft” index 5, which identifies the pilot-controlled aircraft, corresponds to the inclination to the right (clockwise) of the vertical line symbolizing the keel of the aircraft, and the inclination to the left (counterclockwise) corresponds to the negative value of the angle of roll.

The pitch angle and the slip angle for the Leader 4 and Airplane 5 indices in the symbol generator (HS) 15 are represented by a visualizing signal of simultaneous indication in the form of a triangle. The base of the triangle is equal to the length of the horizontal straight line symbolizing the wings of the aircraft, and the position of the top of the triangle corresponds to the value of the pitch angle and glide angle in the coordinates of the moving coordinate system "pitch angle - glide angle" for the "Leader" 4 and "Airplane" 5 indices, respectively. Visually, on the display field 3 of screen 1, with a positive pitch angle and zero glide angle, the top of the triangle is located on a vertical straight line that symbolizes the keel of the aircraft (Fig. 5). A fragment of the flight of the aircraft, visualized on the display field 3 of the screen 1 for the indices "Leader" 4 and "Airplane" 5, depicts a positive pitch angle at zero glide angle and zero roll angle (Fig. 5). With a negative value of the pitch angle, the top of the triangle is located on a straight line, symbolizing the continuation of the keel of the aircraft in the opposite direction (Fig.6). A fragment of the flight of the aircraft, visualized on the display field 3 of the screen 1 for the indices "Leader" 4 and "Airplane" 5, depicts a negative pitch angle at zero glide angle and zero roll angle (Fig.6).

The pilot on the display field 3 of screen 1 sees the glide angle at zero pitch angle as the point of the top of the triangle with zero height, located on the horizontal line, which symbolizes the wings of the aircraft. The distance between the vertical straight line symbolizing the keel of the aircraft and the point located on the horizontal straight line symbolizing the wings of the aircraft in the coordinate system “pitch angle - glide angle” visualizes the magnitude of the glide angle for the Leader index 4 and for the Airplane index 5 At a negative glide angle, the point is located to the right of a vertical straight line symbolizing the keel of the aircraft, showing the pilot the left glide of the aircraft. Fragment of the flight of the aircraft on the display field 3 of the screen 1, when the indices "Leader" 4 and "Aircraft" 5 depict left slip at a zero pitch angle and zero roll angle (Fig. 7). With a positive angle of glide (Fig. 8), the point is located on the left relative to the vertical straight line symbolizing the keel of the aircraft, showing the pilot the right glide of the aircraft. A fragment of the flight of the aircraft on the display field 3 of the screen 1, when the indices "Leader" 4 and "Aircraft" 5 depict a positive glide angle at a zero pitch angle and a zero roll angle is shown in figure 8.

The proposed scheme for interfacing aircraft systems with an aerobatic display indicator (Fig. 3) and a functional diagram of a aerobatic display indicator (Fig. 4) form any possible combinations of the simultaneous presentation of the estimated pitch angle, the estimated slip angle and the estimated roll angle on the display field 3 of the screen 1 for the Leader index 4 and the current pitch angle, the current slip angle and the current roll angle for the Airplane index 5.

The ability of a pilot to see combinations of the simultaneous presentation of pitch angle, glide angle and roll angle for the Leader 4 index and the Plane 5 index provides him (the pilot) reliability and flight safety. The display field 3 of screen 1 (Fig. 9) shows a fragment of an aircraft flight while simultaneously indicating a positive pitch angle and left slip at a zero roll angle for the Leader index 4 and the Airplane index 5. In the presented intuitive image of a geometric shape angles, the pilot instantly determines the angular position of his aircraft, visualized by the index "Airplane" 5, and the spatial position relative to a given flight path according to the position of the index "Leader" 4 on the display field 3 of screen 1.

A fragment of an aircraft flight with simultaneous indication of a positive pitch angle and right slip with a zero roll angle is presented for the Leader index 4 and an airplane index 5 in figure 10 of display field 3 of screen 1. A fragment of an aircraft flight with a simultaneous indication of a negative pitch angle and right the slip at zero roll angle is presented for the Leader index 4 and the Plane index 5 in the figure 11 of the display field 3 of screen 1. A fragment of the flight of the aircraft while simultaneously indicating the negative pitch angle and the left I at zero roll angle is represented by an index for "leader" 4 and index "Airplane" 5 in Figure 12, the indicator field 3 of the screen 1.

Indication on the display field 3 of screen 1 of the flight fragment of the aircraft the current positive pitch angle, left slip and current positive roll angle for the Airplane index 5 and simultaneous indication of the angular position of the Leader index 4, which ensures the execution of the fastest (in time) approach maneuver with the parameters of the programmed flight path of the aircraft, specified at a given time by the calculated values of the negative pitch angle, right glide and negative roll angle for the Leader index 4, representing Figure 13 lena indication field 3 of the screen 1.

The “Airplane” index 5 in the proposed flight-control indicator is made movable in a roll angle around its center of symmetry, which allows the pilot to identify the real roll angle of the aircraft controlled by him (the pilot) and at the same time visually evaluate the pitch angle and angle on the moving figure of the “Airplane” index 5 gliding his aircraft on the flight path. Unlike the prototype, the proposed figure of the “Airplane” 5 index rotates around its center of symmetry, while simultaneously visualizing the current angular position of the pilot-controlled aircraft: the current angle of roll of the aircraft, the current angle of pitch of the aircraft, and the current angle of slip of the aircraft.

The designation of the angular position of the index “Airplane” 5 with a positive current value of the angle of heel - γtek, with a positive current value of the pitch angle - υtek and with the left current value of the angle of glide - βtek is presented in the center of the display field 3 of screen 1 in figure 14.

The visualizing signals for the Leader 4 mobile index not controlled by the pilot (Fig. 4) in the HS symbol generator (15) describe: the value of the estimated roll angle is γcalc, the value of the calculated pitch angle is υcalc, the value of the estimated glide angle is βcalc, the aircraft deviation from flight altitude - ΔH, lateral deviation of the aircraft relative to the programmed flight path of the aircraft - ΔZ, predetermined flight speed of the aircraft - Vset, deviation from it ΔV, taking into account the set arrival time at the final destination of the route and the command "remove landing gear" and "release landing gear".

The sign and magnitude of the estimated angle of heel γcalculation is visually presented in the display field 3 of screen 1 by turning the Leader index 4 around its center of symmetry. The value of the positive estimated roll angle for the Leader 4 index is visualized by tilting to the right (clockwise) of the vertical line symbolizing the keel of the aircraft, tilting to the left (counterclockwise) - the negative calculated roll angle is visualized.

The estimated roll angle is γcalc, on the display field 3 of screen 1 is represented by turning the figure of the Leader index 4 around its center of symmetry by the angle ofcircle γcalc, which for the pilot operating the aircraft is the recommended deviation of the aircraft in the angle of heel, which will be faster (according to time) maneuver to minimize the deviation of the aircraft in the lateral direction, relative to the programmed flight path of the aircraft.

The figure 14 shows the position of the figure of the Leader index 4, to which the calculated (roll to the left) calculated angle of inclination - γcalc, which is calculated in the symbol generator (HS) 15 - provides a maneuver to minimize (in time) the deflection of the aircraft in the lateral direction relative to the programmed flight paths of the aircraft.

In director automatic flight control mode, i.e. Acting as a pilot operator, the pilot observes on the display field 3 of screen 1 the change in the mutual angular position of the Leader index 4 and the Plane index 5. If the pilot wants to intervene in the flight control process, he enters the manual flight control mode, transmitting this command for execution in the automatic flight control system (SAUP) 10.

The pilot, controlling the controls of his aircraft and, accordingly, changing the current roll angle, current pitch angle and current glide angle, visually observing on the display field 3 of screen 1 a change in the shape of the “Airplane” index 5, identifying the angular position of its real aircraft and the change in angular and spatial position of the Leader index 4, which visualizes the deviation of the aircraft from the programmed flight path, achieves a combination of the Leader 4 index and the Plane 5 index in shape, size and position.

In flight, the Leader 4 index in real time on the display field 3 of screen 1 reflects the flight situation, showing the pilot deviations in angles and space from the programmed flight path. The Leader index 4 form shown in FIG. 14 is indicated with a negative value of the estimated roll angle γcalculation, with a negative value of the calculated pitch angle υcalc and with a right (positive) value of the calculated pitch angle βcalc in its moving coordinate system “pitch angle - glide angle”. The pilot in the form of the Leader index 4 instantly presents (in the space of the Earth's coordinate system) the proposed maneuver for his aircraft and, if necessary, the pilot performs the maneuver by correcting the current angular position of his aircraft (γtek, υtek, βtek) to the angular position proposed by the index "Leader" 4 (γcalc, υcalc, βcalc), controlling the flight on the display field 3 of screen 1.

The symbol generator (HS) 15 decreases or increases the Leader index 4 depending on the difference between the values of Vtek - the current value of the aircraft speed vector and Vreach - the set value of the aircraft speed vector.

The speed difference ΔV = (Vad-Vtek) determines the coefficient of the scale of the flight speed of the aircraft mV. When the current value of the speed vector of the aircraft Vtek is less than the programmed vector of the speed of the aircraft Vreach, the index "Leader" 4 decreases in size - is "deleted" (Fig.15). In figures 15, 16, 17 it is important for explanation to show the size of the Leader index 4 and not to focus on other changes in the Leader index 4 that occur when the speed difference ΔV. When the current value of the speed vector of the aircraft Vtek is greater than the programmed target speed vector of the aircraft Vreach, the index "Leader" 4 increases in size - "approaches" (Fig. 16). When the current value of the speed vector of the aircraft Vtek is equal to the programmed set of the speed vector of the aircraft V back, the index "Leader" 4 has a geometric size equal to the geometric size of the index "Airplane" 5 (Fig.17).

The Leader index 4 with values of the angular position (γcalc, υcalc, βcalc) and converted by the coefficient of scale of the flight speed of the aircraft mV moves along the display field 3 of screen 1 depending on the values of the scale factor of the deviation of the flight altitude of the aircraft mH and the scale factor of the lateral deviation of the aircraft mZ. When the coefficients of the deviation scale mH and mZ exceeding the scale for representing the spatial deviations of the aircraft flight path in the display field 3 of screen 1, the Leader 4 index does not go beyond the display field 3 of screen 1, but remains at the boundary of the display field 3 of screen 1 and is indicated by blinking light indication. Flashing light indication is provided by standard features of programming language operators for KPI 9.

The imaginative roll-pitch-height-slip complexity for the Leader 4, Aircraft 5, and Radio Altitude 6 indexes covers all the possibilities of visual representation of the flight path parameters of the aircraft on the display field 3 of the CPI screen 1.

The flight of an aircraft with a current speed greater than the programmed flight speed, with a negative lateral deviation from the given trajectory and with an excess of altitude, is shown in Figure 18. The spatial and angular position of the Leader index 4 on the display field 3 of screen 1 tells the pilot the quickest way out of this situation: reduce the current pitch angle to a negative value, reduce the current roll angle to a negative value, correct the current slip angle to positive (right slip).

When flying the aircraft at a speed close to the programmed one, without deviation in flight altitude and without deviation in the lateral direction, the pilot will see intuitive (Fig. 19) images of the current flight path on the display field 3 of screen 1. To correct the current flight path for the pilot (as the figurative figure of the Leader index 4 suggests), it will be necessary to reduce the current roll angle to a negative value.

A fragment of an aircraft flight with a current negative pitch angle, at a height less than the programmed path height and at a flight speed less than the programmed flight speed, is shown in Figure 20. An intuitive figurative prompt "increase the current pitch angle to a positive value and increase the current speed the flight "the pilot will perceive unmistakably, which will ensure a trouble-free exit from the situation even in extreme flight conditions, when there is no time to make a decision.

A fragment of the flight path of the aircraft at the time of landing, when the current flight speed of the aircraft controlled by the pilot is equal to the programmed flight speed, the flight altitude, the angular position of the aircraft close to the programmed values are shown in figure 21. An intuitive figurative prompt reminds the pilot that according to the flight program when landing at the moment it is necessary to execute the command "release the landing gear", so the pilot will never make a landing with emergency consequences without landing gear. The commands “remove the landing gear” and “release the landing gear”, which are given only during takeoff and landing, will not distract the pilot’s attention from the main goal of the flight, removing the psychophysiological load, since in this phase of the flight the landing gear is indicated on the Leader 4 index and index Aircraft "5 is missing. The proposed functional diagram of the flight indicator (Fig. 4) allows the Leader 4 index to move freely horizontally and vertically in the display field 3 of screen 1, visualizing the spatial deviations of the aircraft relative to the programmed flight path; allows you to rotate around the center of symmetry and similarly change its shape with a figurative image of the estimated value of the angle of heel, the estimated value of the pitch angle, the estimated value of the angle of slip in accordance with the coefficient of scale of the speed of flight. When the aircraft is on the desired trajectory, flies with the required roll angle, pitch angle, slip angle and at a given speed, the Leader 4 pointer is aligned with the Airplane 5 index both in position and size.

This intuitive display makes piloting easier. The proposed KPI indication, visualized by the angular position of the mobile pilot-controlled index “Airplane” 5 together with the “radio height” index 6, forms a new imaginative complexity “roll-pitch-height-glide”, which is easily and guaranteed to be correctly perceived by a pilot of any skill in any weather conditions and at any altitude under conditions of limited time to make the right decision for the control of the aircraft, which provides the pilot of any skill with his inextricable control over the flight of his aircraft and a complete lawsuit li ne of pilot errors, accidents and catastrophic flight of consequences associated with the loss of pilot spatial orientation in the management of the aircraft in extreme flight conditions.

The ability to control the flight of an aircraft with the indication of a moving index “Leader” and a moving index “Aircraft” that we offer guarantees the pilot a safe flight mode in the most difficult extreme flight conditions, since the visualization of the parameters of the flight deviation of the aircraft from the programmed path in the character generator 15 covers all possible options indications of the Leader moving index (the carrier of all flight restrictions), which ensure safe flight control of the aircraft and exit from any extreme situation, even so there is no time to make the right decision.

In the present invention, it is important to show the ability to see the current roll angle, pitch angle and glide angle of the aircraft controlled by the pilot on the navigation field 3 of the KPI screen 1 and associate these angles with the “Airplane” index 5. On the KPI screen, the pilot will see the actual angular position of his aircraft in space, determined by the current roll angles, pitch angle and calculated current glide angle.

This is the basis for a safe indication of the proposed flight indicator.

On this cycle of operation of the flowchart (Fig.3) is completed.

The inventive flight control indicator allows you to provide:

- the exception of aerobatic errors, accidental and catastrophic consequences of the flight associated with the loss of spatial orientation by the pilot;

- accident-free exit in the shortest possible time from any of the most difficult extreme situations in the face of a strong psychophysiological load, when there is no time to think and make a decision;

- increasing the visibility of the current flight parameters related to instrument control of the aircraft in the director's flight with automatic control mode, when the pilot performs the functions of the “pilot-operator” and in the director’s flight with manual control of the aircraft, as well as when the pilot disables director’s flight control and controls Aircraft in manual free flight mode at its discretion;

- excellent perception by the pilot of the magnitude and sign of the current roll angle, pitch and glide angle of the “Airplane” index in the cockpit coordinate system (exactly the same as in visual flight in the earth system);

- perception by the pilot of the controlled index “Airplane” as the aircraft of the leader, but at the same time clearly presenting and managing its full spatial position;

- easy and guaranteed error-free perception of imaginative complexity ("roll-pitch-height-glide") by a pilot of any skill in any weather conditions and at any height, because it does not distract his attention when piloting an aircraft on an artificial horizon horizon, an aircraft heading indicator, pitch angle calibration, angle a calibration, a colored picture of the ground-to-sky horizon (to evaluate the quantitative value of the listed parameters, they require sequential reading of information from the corresponding scales, which leads to increase the time to estimate the spatial position of the aircraft by instruments and reduce the time to assess the spatial position of the aircraft and take the right control actions), which in general om leads to increased safety.

Claims (4)

1. A flight indicator containing a screen on which a reference index in the form of a stylized image of an airplane when viewed from the rear with the landing gear (“Aircraft”) fixed in relation to the center of the display field of the screen is displayed, indicating the current position of the aircraft in space, the moving index is displayed on the screen in the form of a stylized image of an airplane when viewed from the rear with the landing gear extended, indicating the desired position of the aircraft in space (“Leader”), having the ability to rotate around its center of symmetry, as well as vertical and horizontal movements relative to the “Airplane” index, a symbol generator connected to the screen, “Leader” mobile index controls, made in the form of “Leader” characteristics calculation blocks, the inputs of which receive signals from aircraft systems, and from the outputs of which the symbol generator receives signals in accordance with the magnitude of the control error in height, ensuring the Leader index moves along the display field in the vertical direction, along the pitch angle and rotates it around the center of symmetry in correspondence with the error in roll angle, increase or decrease in linear dimensions of the Leader index with an increase or decrease in accordance with a given flight speed in such a way that at zero error values for all controlled parameters, the Leader index is combined with the Airplane index, characterized in that the Airplane index is rotatable around its center of symmetry, and the stylized image of the Airplane and Leader indexes is made in the form of one horizontal line symbolizing the wings of an aircraft, and one vertical line, symbolizing the keel of the aircraft and intersecting the horizontal line in its center at a right angle, and is additionally equipped with a unit for calculating the parameters of the current sliding angle, a unit for calculating the estimated angle of heel, a unit for calculating the estimated angle of sliding, a unit for calculating aircraft deviation in flight altitude and coefficient the scale of the deviation of the aircraft flight altitude, the unit for calculating the value of the calculated pitch angle, the unit for calculating the lateral deviation and the scale factor for the lateral deviation of the aircraft, to the inputs of which receives signals from aircraft systems, and the outputs of which are connected to the inputs of the symbol generator, and is also configured to display the radio altitude index and a fixed uneven scale of the value of the flight altitude, which is displayed on the vertical side of the border of the display field of the screen with a zero height value, located at the level horizontal line passing through the center of the display field of the screen, while both the index “Aircraft” and “Leader” are made with the ability to simultaneously display the current sliding angle and angle engagement of the “Airplane” index and deviation from the given slip angle and pitch angle of the “Leader” index by indicating a triangle whose base is equal to the length of the horizontal straight line symbolizing the wings of the aircraft, and the position of the triangle apex corresponds to the current value of the pitch angle and the slip angle of the “Airplane” index and a deviation from a predetermined pitch angle and a slip angle of the Leader index. 2. The flight indicator according to claim 1, characterized in that the horizontal and vertical lines forming the images of the Leader and Airplane indices are made with different thicknesses and brightness. 3. The flight indicator according to claim 2, characterized in that when the deviation from the specified parameters of the lateral deviation and the height exceeds the maximum possible for indication, the Leader index remains at the boundary of the display field of the screen and by periodically changing the brightness (blinking) warns of excess lateral deviation and height. 4. The flight indicator according to claim 3, characterized in that the Leader and Airplane indices are configured to indicate the removal of the landing gear when the aircraft’s flight altitude is higher than the height of the programmed flight without landing gear and execution of the “release the landing gear” command by indicating under the horizontal lines symbolizing the wings the “Leader” and “Airplane” indices of the landing gear in the form of two lines at a time when the aircraft’s flight height is less than the height of the programmed flight without landing gear.

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