RU44842U1 - INFORMATION TEAM LEADER SYSTEM - Google Patents

Abstract

The utility model relates to aeronautical engineering (avionics) and can find application in the creation of flight and navigation equipment for airplanes and helicopters for flights in high-precision maneuvering modes in low-altitude flights over difficult terrain, approach and landing on a low-equipped airfield in difficult conditions.

An information command-and-lead system containing an on-board geographic information system, a module for preventing dangerous flight conditions, multifunction indicators, an aircraft navigation system (helicopter) calculator, an integrated aircraft control system, a collimator aircraft indicator and mode controls for integrating a software module for constructing an autonomous glide path for target designation modes , correction of information and the formation of course and glide path information with a software module amoletovozhdeniya provides rational combination of perceptual space signal and parametric data, improving control accuracy and safety of flight modes approach and landing on poorly equipped airfields and takeoff run and in difficult conditions by Firmware:

- target designation of the landing site or landmark (geo-point),

- formation of runway and autonomous glide path parameters with the help of KAI and autonomous navigation calculator,

- correction of the coordinates of the aircraft and the parameters of the path),

- formation of course-glide path and command-leader information for semi-automatic landing control along an autonomous glide path,

- aiming by the velocity vector in the cursor-glide path during landing,

- piloting with aiming in the runway by the velocity vector during landing,

- aiming the velocity vector along the centerline of the runway during take-off and take-off of the aircraft,

- formation of runway and autonomous glide path parameters, course and glide path information and command signals for semi-automatic landing control along an autonomous glide path to a low-equipped airfield in difficult weather conditions using cartographic information,

- the formation of control information on the removal of the aircraft from dangerous states of trajectory maneuvering

approach and landing using cartographic information and an integrated management system.

The implementation of all of the above functions is ensured by the fact that an airplane indicator is connected to the airplane navigation calculator through an interface module, which contains an imaging unit and an electron-optical unit, and mode controls that include a targeting mode button, a two-channel joystick for controlling the image movement with an aiming mark, and a snap button the selected landing site and the heading unit of the virtual runway course, and the software module for constructing an autonomous glide path It is combined with the software module of navigation.

Such a technical solution for providing information about the command and leader support for the crew of an aircraft in difficult flight conditions makes it possible to approach and land the aircraft at a low-equipped airfield without categorized radio and lighting systems, improve flight safety conditions, accuracy of trajectory maneuvering and increase the efficiency of the use of aircraft for various purposes.

The proposed concept of constructing an information management field system is modeled on the ergonomic stand of NIIAO. The obtained results confirmed the pilot's effective work in high-precision maneuvering modes in low-altitude flight, approach and landing of the aircraft, as well as when solving special. tasks.

These technical proposals aroused the interest of specialists of KB them. Ilyushin, Yakovleva, Tupolev, Beriev, OAO Sukhoi, and MMZ Mikoyana.

The nearest implementation is expected at the next modernization of IL-114 aircraft equipment.

Description

The utility model relates to aeronautical engineering (avionics) and can find application in the creation of flight and navigation equipment for airplanes and helicopters for flights in high-precision maneuvering modes in low-altitude flights over difficult terrain, approach and landing on a low-equipped airfield in difficult conditions.

When flying in difficult weather conditions at extremely low altitudes above a difficult terrain, a large number of flight accidents occur due to the pilots losing their idea of their spatial position and the trajectory movement of the aircraft.

Known information is a command and leader system (see RF patent, No. 2145725, CL G 05 D 1/00, 1995), containing an on-board geographic information system, a system for warning dangerous flight conditions, multifunction indicators, a computer for airplane navigation (helicopter driving), an integrated control system of the aircraft, interconnected via interface modules, which allows to improve flight safety conditions, accuracy of trajectory maneuvering and increase the efficiency of the use of aircraft about destination ,. The system provides for flight control using an electronic card.

However, this system does not provide, to a sufficient extent, the approach and landing of an aircraft at operational low-equipped aerodromes, when control is complicated due to the lack of a ground course and glide path system and difficult weather conditions, and also because in the landing mode there is a need for intensive alternating control of flight parameters located on the dashboard of the pilot's pilot, and outside the cabin, i.e. a rational presentation of information to the crew for articulated perception of the space outside the cabin, parametric and signal information located on the pilot’s PD is not provided.

The objective of this utility model is to create a control and information field system that enables the pilot to simultaneously see the main flight parameters, off-cabin conditions and dangerous conditions, to form control actions appropriate to the situation during flights on high-precision maneuvering modes in low-altitude flight over difficult terrain, approach and landing landing on a low-equipped airfield, and, therefore, to improve flight safety in difficult conditions.

One of the conditions for the high efficiency of information support in the approach and landing control mode is the creation of an opportunity for the pilot to receive the necessary information in a form that ensures its most quick and error-free processing without interruption from observing the external visual situation and

to carry out the necessary correction of information coming from on-board sensors.

The task is achieved by the fact that in the information-command and leader system containing an on-board geo-information system, a module for preventing dangerous flight conditions, multi-function indicators, an airplane navigation system (helicopter) calculator, an integrated aircraft control system, a collimator aviation indicator is connected to the airplane navigation calculator through an interface module comprising an imaging unit for the reticle and other information, and electron-optical lock, and mode controls, containing a targeting mode button, two-channel aiming mark control joystick, an aiming mark binding button for a selected landing site and a virtual runway heading unit, and an autonomous glide path building module for target designation, information correction and course-glide path formation The information is bundled with the airborne software module.

When conducting patent research, no solutions were found that are identical to the declared one, and, therefore, the claimed utility model meets the criterion of "novelty."

We believe that the information presented in the application materials is sufficient for the practical implementation of the utility model.

The essence of the proposed utility model is illustrated by graphic materials on which:

- Figures 1 and 1a are a block diagram of an information command-leader system for providing an approach and landing of an aircraft on a low-equipped airfield using a collimator aviation indicator and additional mode controls;

- figure 2 and 3 presents the information frames of the collimator aviation indicator for target designation, approach and landing for display options view "from plane to ground" (figure 2) and "from ground to plane" (figure 3);

- Figures 4 and 5 show information frames of a collimator aviation indicator for target designation, approach and landing for display options such as "from the plane to the ground" (Fig. 4) and "from the ground to the plane" (Fig. 5) against the background land.

The information command and leader system (Figs. 1 and 1a), contains an on-board geographic information system 1, a module for preventing dangerous flight conditions 2, multi-function indicators 3, a computer for airplane navigation (helicopter) 4, an integrated control system for the aircraft 5, interface modules 6, a collimator aviation indicator 7, mode controls 8, reticle forming unit 9, electronically optical unit 10, target designation mode button 11, dual-channel joystick for controlling the sight brand 12, snap button to the landing site 13, heading unit BUSH 14, module for constructing an autonomous glide path 15, module for airplane navigation

16, a complex of avionics 17.

On-board geographic information system 1 is designed to provide modules of the information command-leader system and subsystems of the complex of on-board equipment with digital cartographic information in real time for the formation of:

- an electronic moving map displaying the aeronautical situation;

- a pseudo-volumetric image in front of the underlying relief of the underlying surface for manual piloting in the low-altitude flight mode with bypassing and flying around obstacles;

- profile of the relief along the predicted trajectory in the low-altitude flight mode and approach;

- parameters of the runway and runway and autonomous glide path, course and glide path information and command signals for semi-automatic landing control along the autonomous glide path to a low-equipped airfield in difficult weather conditions using cartographic information,

- control signals and commands for taking the aircraft away from dangerous states of trajectory maneuvering during approach and landing using cartographic information and an integrated control system.

The module for preventing dangerous conditions of flight 2 is designed to provide information to increase the level of safety and flight efficiency, to indicate dangerous conditions of trajectory control and to signal about a dangerous approach to the ground.

Multifunctional indicators 3 based on graphic processors and color liquid-crystal displays Za and 36 are designed to provide the crew with command and leader information, navigational and tactical conditions and an electronic aeronautical chart, as well as information about the necessary control actions during piloting and high-precision maneuvering at extremely low altitudes, when approaching.

The formation of the mnemo frame of the flight information of command and leader information ensures that the basic flight information, direction and glide information for controlling landing on a low-equipped aerodrome using an autonomous glide path and a pseudo-volume image of dangerous states approaching the terrain, as well as information about the required control actions during piloting and high-precision maneuvering at extremely low altitudes.

The snapshot is based on the introduction of a new type of horizon, which uses images of the symbols of your aircraft and the “leader” to indicate to the pilot visual command-and-leader information about the given motion parameters according to the “do as I” principle.

On the mnemonic frame of an aeronautical chart with navigational and tactical conditions, cartographic information is presented in the form of an aeronautical chart image in the selected coordinate system and at the selected scale, which is color-coded depending on hazardous areas near the terrain and terrain features. In the landing mode on a low-equipped airfield, in the absence of course-glide-slope ground radio equipment and the presence of on-board digital cartographic information, the multimadra of multifunctional indicators can be used by the pilot to target the landing site and form an autonomous glide path and virtual runway symbol parameters displayed on the collimator aviation indicator 7.

The navigation calculator 4 is designed to provide information for solving the problems of navigation, navigation, formation of an autonomous glide path when landing on a low-equipped aerodrome, warning of dangerous flight conditions, controlling high-precision maneuvering and generating command-leader information using data from the onboard equipment complex 17.

The functioning of the calculator when interacting with the database, indicators and mode controls is provided by the software module for constructing an autonomous glide path 15 for target designation modes, information correction and formation of course and glide path information and the aircraft navigation software module 16.

The computer 4 is connected to the on-board geographic information system 1, the hazardous flight warning system 2, the multi-function indicators 3, the integrated control system of the aircraft 5, the collimator aviation indicator 7, the mode controls 8 and the on-board equipment complex 17 through interface modules 6 that provide input control -input and operation modes.

An integrated control system for the 5th aircraft provides semi-automatic and manual control approaches for landing and landing along an autonomous glide path to a low-equipped aerodrome and automatic control of removal from dangerous flight conditions.

Interface modules 6 are designed to provide I / O control and system operation modes.

The collimator aviation indicator 7 in the approach and landing control modes provides optical combination of instrumental flight and navigation information with the external visual environment, which allows the pilot to exclude the transfer of gaze, re-accommodation and re-adaptation of the visual analyzer and, thus, reduce the discreteness of perception of instrument information when

distracting attention from the dashboard to extra-cab objects during the approach and landing.

On the collimator aviation indicator are displayed:

- flight-navigational flight parameters controlled by the aircraft navigation module 16,

- information about the position of the autonomous glide path, target designation of the landing site and landmark (geo-point), information correction, as well as course and glide path information generated and controlled by the autonomous glide path module 15 in the approach and landing modes for the low-equipped airfield.

The course and glide path information for landing on an autonomous glide path is also displayed on the multifunctional on-screen indicator 3 on the mnemo frame of the aerobatic command-leader information

Considering that, when landing on operational low-equipped aerodromes, glide path formation is difficult, the sighting mark 31, glide path symbol 32, virtual runway (33) symbol and current speed vector symbol 25 calculated taking into account the angle of inclination of the trajectory are additionally displayed on the collimator aviation indicator . The aiming mark is combined by the pilot with the start of the runway (visible through the windshield) in the interest of obtaining additional information that is used in the on-board computer to form the glide path. When piloting with the velocity vector aiming at the landing stage, the aiming mark is combined with the runway landing sign, and during take-off, with the center line of the visible part of the runway.

The location and form of presentation of information on the collimator aviation indicator provides the most rational conditions for the perception of the off-cabin situation, parametric and signal information, correction of the parameters of the trajectory movement and the formation of the flight image, in accordance with which the pilot exercises control actions.

Information frames shown in figure 2, 3, 4 and 5 contain:

current and set speed counters - pos. 18;

a trend in speed - pos. 19;

current and set height counters - pos. 20;

variometer - pos. 21;

pitch scale - pos. 22;

course scale - pos. 23;

airplane silhouette - pos. 24;

index of the “velocity vector” - pos. 25;

range counter - pos. 26;

radio altitude indicator - pos. 27;

movable "keel" - pos. 28;

roll scale - pos. 29;

overload and slip restriction index - pos. thirty;

reticle - pos. 31;

glide path symbol - pos. 32;

runway symbol (runway) - pos. 33;

pressure meter at the height of the airfield - pos. 34;

warning field - pos. 35.

The runway symbol (pos. 33) is formed as a trapezoid, the vertices of which are projections onto the frontal plane of the dimensional points of the airdrome selected during target designation or calculated. The width of the aerodrome in the calculation is 45 (40) meters, the length depends on the current configuration of the aircraft. Under the condition that the length of the estimated airfield does not exceed the actual (visually visible), landing is possible.

The glide path symbol (key 32) is a line connecting the estimated landing place (touch point of the calculated runway) with the current point of entry into the glide path (continuation of the runway axis from the cut-off point with an angle of inclination), but not further than the fourth turning point at long ranges. The size of the crosshair corresponds to the size of the slice of the course-glide zone at this range. With the capture of radio equipment of the airfield (if any), course and glide path frames appear, respectively.

The control modes 8 for the formation of the parameters of the virtual runway and the autonomous glide path contain:

- button target designation 11, designed to enable / disable (reset) target designation mode;

- the joystick 12 is potentiometric or tensometric, located on the helm under the thumb of the right hand, the two-coordinate signals of which provide the movement of the aiming mark along two axes;

- button snap to the landing site (landmark) 13, located on the helm under the thumb of the left hand, which is the binding of the runway and the calculation of the autonomous glide path;

- course runner 14 operational runway (potentiometric or digital).

It is possible to locate the joystick, the above buttons and the heading switch for the operational runway on an autonomous remote control and use any two-coordinate analog switch instead of the joystick (similar to the crosshair control mechanism). The reticle control joystick is used during approach, during the runway passage for correction of glide path parameters, during landing and take-off. Management of the reticle can be integral (brand movement at a speed proportional to the value of the joystick deviation) or positional.

Information team leader system operates as follows.

The flight control of the aircraft is carried out by the crew using the controls of the integrated control system of the aircraft and the controls of the system modes. During the flight, the crew receives information about the flight from multifunctional indicators, KAI and visually through KAI about the ground situation.

The mode of formation of runway and autonomous glide path parameters using KAI in autonomous mode is used to select a landing point, including at a previously unknown airfield (for emergency landing).

The inclusion of this mode is carried out in conditions of visual visibility of the area. An aiming mark appears in the center of the KAI screen, displaying the position of the line of sight (LV). Using the joystick, the pilot moves it around the screen until it is visually aligned with the beginning of the terrain selected for landing. The coordinates of the line of sight (marks) are calculated in a gyro-stabilized (from the inertial system of the aircraft) horizontal coordinate system along the roll and pitch relative to the construction axis of the aircraft. This ensures the filtering of their own movements (oscillations) of the aircraft and provides the convenience of label management. At the end of the target designation, the pilot presses the “snap” button, thereby giving the command to the computer calculator of the aircraft navigation system to calculate the coordinates of the runway and the autonomous glide path. Based on the hypothesis of piecewise flat and horizontal ground, as well as on the basis of the readings of the radio altimeter and signals about the position of the drug in space, the computer calculates by geometric calculations the position of the start of the runway relative to the aircraft on the “virtual” earth’s surface and, accordingly, the distance to the cutoff her lateral evasion.

Initially, the runway heading is taken equal to the current heading (or the current heading line). Further, it is possible to calculate the coordinates of the runway ends taking into account the minimum range required for a given flight configuration and VHS width and the construction of an autonomous glide path with an inclination angle of 2.7 °.

The calculated parameters of the runway and the autonomous glide path at the time of releasing the snap button:

- are recalculated by the calculator into the screen (for KAI) coordinate system for rendering the runway and glide path;

- the coordinates of the point selected on the “ground” are recalculated to the current coordinates of the drug and it is accompanied by the symbol of the drug. Further, using the runway heading switch, you can “deploy” the strip so that it better “lies down” on the ground (coincides with the visually visible one, does not include objects that are dangerous for aircraft landing), etc. The calculation results are displayed on KAI.

The data obtained are used in the preliminary calculation of the maneuver for the approach with a straight line and with a positive assessment of the possibility of its implementation, and are also used to control the “glide path”. In the process of approaching the runway, the pilot, holding the “Snap” button, can adjust the calculated position of the runway, coordinating with the visually visible, thereby parrying the errors resulting from:

- optical errors KAI;

- designation errors;

- calculations in the airplane calculator,

as well as due to non-flatness and non-horizontalness of the aerodrome area.

If it is impossible to complete an approach approach with a straight line without going beyond restrictions, the aircraft navigation module 16 builds a maneuver for withdrawal to the point of the third (fourth) turn. Next, the process of adjusting target designation is repeated in a similar way.

With insufficient pilot confidence in the accuracy of target designation, the approach can be performed as follows. Target designation is carried out, followed by maneuver to exit the target runway, passage over the “lane” with precise stabilization of the echelon (for example, 500 m) in a baroinertial manner and simultaneous measurement and registration of radio altitude. During the passage of the “strip” alignment, the coordinates are corrected to clarify the landing site and at the same time the readings of the radio altimeter are processed to determine the profile of the relief along the axis of the runway. The estimated error in the point calculation of the relief, taking into account obstacles, is 10 m (7 m is the error of the RV + 3 m, the error in stabilizing the echelon by the baroinertial method) can be reduced when calculating the surface slope by mathematical processing methods. At the same time, the barocorrection value for pressure at the height of the airfield can be calculated.

It should be noted that the above-described method for correcting the coordinates of the aircraft’s location refers to the methods of relative navigation implemented by calculator 4 together with the inertial system, altimeters and KAI, without the use of satellite and radio systems. However, it is necessary to consider a simpler approach approach to low-equipped aerodromes with previously known coordinates.

If the geographical coordinates, threshold height and runway course are known in advance, the use of a satellite navigation system (SNA) or an inertial system together with the SNA allows you to enter the airfield area and approach using a pre-built autonomous glide path. Further provided for the capture of the RTS airfield and landing. However, if the aerodrome is not equipped with RTS or it is impossible to use them (in case of ground or airborne vehicle failure), then if there are errors in determining the location of the aircraft, the maneuver will be built with an error (up to 50-100 m for the non-differential operating mode of the SNA). Coordination of coordinates can be carried out using the second SNA receiver installed at the aerodrome, and the corresponding equipment for transmitting data to aircraft, and if they are absent according to KAI.

For this, it is necessary that, when approaching the aerodrome and falling into the estimated landing point in the KAI field of view, the calculator should provide the calculated (expected) aerodrome coordinates and glide path parameters on the KAI regardless of the conditions of its visual visibility. When a visually visible strip appears and does not coincide with the calculated one, the pilot must use the KAI sighting mark to indicate the visually visible landing site (midway section of the runway). Then, by deviating the line of sight from the aircraft’s construction axis (KAI center), the coordinate reckoning error is calculated and the number reckoning of the aircraft’s location is corrected.

In the modes of forming parameters of the runway, autonomous glide path, course and glide path information and command signals for semi-automatic landing control along the autonomous glide path, as well as control information for taking the aircraft away from dangerous conditions

trajectory maneuvering during approach and landing using cartographic information and an integrated control system, a database and algorithmic support for the on-board geoinformation system 1, hazard warning module 2, indicators 3 and 7, module for constructing an autonomous glide path 15, calculator 4, controlled through interface modules 6.

For early warning of an airplane collision with the earth's surface, the developed algorithm implements:

1) Determination of the current position of the aircraft in the coordinate system of a digital map.

2) Selection from the array of heights of the elevation value of the terrain under the plane.

3) Calculation of the basic parameters of the dynamics of low-altitude flight: the time and lead distance, the distance of the forecast flight grid, the height of the beginning of the relief monitoring zone (relative to sea level), the grid pitch in range, and geometric height.

4) Generation of a flat lead grid taking into account aircraft roll, creation of a curved grid when predicting a curved path.

5) Pulling a grid of heights on a relief.

6) Creating a pseudo-relief taking into account the flight speed and highlighting the majorant in the virtual field of view (in the monitoring area).

7) Data selection in the monitoring zone:

- calculation of the coordinates of the highest point in the coordinate system of the grid and the array of unit distance vectors to points at the grid nodes in the observer coordinate system;

- the formation of an array of points in the grid nodes in the observer screen coordinate system for display on the indicator;

- calculation of normal vectors to the surface of the relief.

8) Formation of the conditions of withdrawal with the transition to the automatic control mode of withdrawal from the longitudinal majorant of the monitoring zone of the terrain.

9) Highlighting the majorant’s height at a critical point of the highest elevation of the relief (a given flight altitude above the dangerous majorant’s height in the monitoring zone) and solving the problem of controlling an airplane in low-altitude flight.

10) Performing graphical procedures for visualizing the state of the flight process on the screen indicator and KAI.

Thus, the information command and leader system, combined with a collimator aviation indicator (indicator on the windshield) and system mode controls, provides improved accuracy and safety of approach and landing at low-equipped aerodromes in difficult conditions by targeting the landing site, formation of runway parameters and autonomous glide path using KAI in autonomous mode, the formation of command signals for controlling landing along an autonomous glide path, correction of the coordinates of years Tel'nykh aparata, aiming velocity vector in an Instrument glisadnoe window when landing, flying velocity vector with aiming at landing at a runway rational combination pilot perception space

(outside the cabin environment), parametric and signaling information, as well as increasing the regularity of flights in difficult weather conditions through the possibility of reducing meteorological minimums of aircraft and increasing the accuracy and safety of flights at the stages of take-off and landing at low-equipped aerodromes without categorized radio and lighting systems for take-off and landing. The location, form and composition of the parametric and signaling information presented on the collimator aviation indicator and combined with the real off-camp environment provide the pilot with the most rational conditions for perceiving and comprehending the received data to form a flight image, according to which the pilot performs control actions to correct the parameters of the trajectory movement the plane.

The proposed concept of constructing an information management field system is modeled on the ergonomic stand of NIIAO. The obtained results confirmed the pilot's effective work in high-precision maneuvering modes in low-altitude flight, approach and landing of the aircraft, as well as when solving special. tasks.

These technical proposals aroused the interest of specialists of KB them. Ilyushin, Yakovleva, Tupolev, Beriev, OAO Sukhoi, and MMZ Mikoyana.

The nearest implementation is expected at the next modernization of IL-114 aircraft equipment.

Claims (1)

An information command and leader system containing an on-board geographic information system, a module for preventing dangerous flight conditions, multi-function indicators, an airplane navigation system (helicopter) calculator, an integrated aircraft control system, characterized in that a collimator aviation indicator is connected to the airplane calculator through an interface module containing a unit imaging and electronic-optical unit, and mode controls, containing the mode button and target designation, a dual-channel joystick for controlling the reticle, a snap button to the selected landing site and a heading unit for the virtual runway, and a software module for constructing an autonomous glide path for target designation, correction of information and the formation of course and glide path information is combined with a software module for aircraft navigation with the possibility of providing high-precision modes maneuvering in low-altitude flight over a difficult terrain, approach and landing on a low-equipped aer a rodrom without categorized radio and lighting systems for take-off and landing in difficult conditions, flight control using an electronic map and pseudo-volume displays of dangerous states of trajectory control on indicators.