RU43387U1 - VISUALIZATION SYSTEM OF THE SIMULATOR OF THE BATTLE AIRCRAFT VEHICLE - Google Patents

Abstract

The visualization system of a combat aircraft simulator is a technical training tool and is intended for use as part of a combat aircraft simulator (fighter, attack aircraft, combat trainer, combat helicopter) equipped with a “windshield indicator”. The essence of the proposed utility model is that in a visualization system with a projector and a screen, a computer system for generating images of the external visual situation and an “indicator on the windshield”, including a cathode ray tube, a grid, a collimator head and two beamsplitters installed one above the other , a diffusing lens is inserted into the “indicator on the windshield”, mounted on top of the frame of the collimator head and fixed on it with a bracket, and part of the lens is cut at an angle to the optical axis, ver The lower and lower beam splitters are deviated from the normal position by some small angles so that their planes become non-parallel one another and, moreover, a symbol generator, a synchronization and switching unit and a low-voltage power supply are introduced, the first input of the “indicator on the windshield” is connected to the output of the unit low-voltage power supply, the input of which is connected to the simulator's on-board power supply simulation system, the second input of the “indicator on the windshield” is connected to the output of the synchronization and switching unit, the input of which is connected to the output a symbol generator, with its input connected via an interface adapter to the first output of the simulator computing complex, the second output of the simulator computing complex is connected to the input of the computer system to generate images of the external visual environment, the output of which is connected to the projector projecting the image onto the screen, and to the input of the simulator computer system the outputs of the controls of the simulator cabin are connected. The standard mesh is replaced by a training mesh, which differs from the standard mesh in linear dimensions, and antireflection coatings are applied to the reverse sides of the beam splitters.

Description

The proposed utility model relates to technical training aids and can be used in a simulator of a combat aircraft (fighter, attack aircraft, combat trainer, combat helicopter) equipped with a “windshield indicator”.

There is a well-known flight bench for working out the information-control field of the cockpit of promising fighters, made in 2001 by order of Sukhoi Design Bureau (see D.N. Levin, M.G.Shapiro Experience in using a flight bench in the interests of working out the control field of the cockpit of a promising fighter. reports of the second scientific and technical conference "Training technologies and training: new approaches and tasks", Central Aerohydrodynamic Institute named after Professor N.E. Zhukovsky, April 24, 25, 2003, Zhukovsky, Moscow Region, pp. 139-143) . In the stand visualization system, a multichannel projection of visual environment images onto a cylindrical screen and an “indicator on the windshield”, used as a weight-dimensional layout, were used. At the same time, all flight-navigation and sighting information is superimposed on the image of the external visual situation and they are projected onto the screen together, and the pilot looks at the screen through the beam-splitting plates of the “indicator on the windshield”.

The disadvantage of the visualization system constructed in this way is that the pilot does not need to “catch” the exit pupil of the optics with one eye, which greatly facilitates its operation during aiming operations and reduces the level of training after training on such a simulator.

A known visualization system for a modeling stand with a sighting device (see patent RU 2202829 IPC: G 09 V 9/00, 9/30), including wide and narrow field screens and image creation tools, as well as located between the operator and the narrow screen ILS fields (“windshield indicator”) and collimation optics. Imaging tools also include projectors aimed at screens. The technical result is the exclusion of parallax between the HUD marks and the visualized images on the narrow field screen.

The disadvantage of this system is the need to recompact the operator’s vision from infinity to a finite distance each time the operator needs to see something in the cockpit space outside the field of view of the ILS. This creates an additional load on the pilot’s visual apparatus during training, which is not useful, since when piloting real aircraft, re-accommodation of the vision is not required when viewing the lateral visual situation. In real conditions, such re-accommodation has

a place only when the operator is looking from the cockpit to the inside of the cab (for example, to appliances).

The authors were faced with the task of ensuring the use of a really working HLS in the simulator and at the same time ensuring the reproduction of HLS information in the plane of the screen of the visualization system, and not at infinity.

In the proposed utility model, this problem is solved due to the fact that in the visualization system with a projector and a screen, a computer system for generating images of the external visual situation and an “indicator on the windshield”, including a cathode ray tube, a grid, a collimator head and two installed one above another beam splitter, in the “indicator on the windshield” a diffusing lens is inserted, mounted on top of the frame of the collimator head and fixed on it with a bracket, and part of the lens is cut at an angle to the optical axes, and the upper and lower beam splitters are deviated from the normal position by some small angles so that their planes become non-parallel one another, in addition, a symbol generator, synchronization and switching unit and a low-voltage power supply are introduced, the first input of the “indicator on the windshield” is connected with the output of the low-voltage power supply, the input of which is connected to the simulator's on-board power supply simulation system, the second input of the “indicator on the windshield” is connected to the output of the synchronization and switching unit, the input of which is connected the output of the symbol generator, with its input connected via an interface adapter to the first output of the simulator computing complex, the second output of which is connected to the input of the computer system for generating images of the external visual environment, the output of which is connected to the projector projecting the image on the screen, and connected to the input of the simulator computer system exits of controls of a simulator cabin. Moreover, the standard grid has been replaced by a training one, which differs from the standard one by linear dimensions, and antireflection coatings are applied to the back of the beam splitters.

The proposed visualization system for the simulator of a combat aircraft has a set of essential features unknown from the prior art for visualization systems of this purpose. The essence of the utility model is illustrated by figures in figures 1-7. Figure 1 presents the structural diagram of the simulator in terms of reproduction in the exit pupil of the ILS of flight-navigation and sighting information, as well as the external visual situation on the screen of the visualization system;

figure 2 - arrangement of the optical components of the standard ILS;

figure 3 is a simplified optical diagram of the collimator head of the ILS;

figure 4 is a simplified diagram of an optical system that provides the location of the plane of the direct imaginary image y 'of the object relative to the exit pupil of the optics at the required distance of 1 _p .

figure 5 is a drawing of the installation of a scattering lens on the collimator head of the ILS;

figure 6 is a photograph of the ILS on the desktop in front of the screen with the image of the external visual environment, including the image of the target;

7 is a photograph of the same image made from the exit pupil of the ILS. The picture contains symbols of navigation and navigation information, the image of the target is covered with an aiming mark. All images are located in one plane - the screen plane.

Figure 1 shows: visualization system 1, screen 2, projector 3, computer system for generating an image of the external visual environment 4, "indicator on the windshield" 5 (ILS), operator 6, low-voltage power supply 7, synchronization and switching unit 8 , symbol generator 9, controls of the simulator cabin 10, computer complex of the simulator 11, interface adapter 12, on-board power supply simulation system 13. The projector 3 is connected to the output of the computer system to generate an image of the external visual environment 4, connected by its the input with the second output of the computer complex simulator 11; the output of the low-voltage power supply unit 7 is connected to the first input of the ILS 5, connected by its input to the output of the simulator's on-board power supply system 13; the output of the synchronization and switching unit 8 is connected to the second input of the ILS, connected by its input to the output of the symbol generator 9, which is connected via its interface adapter 12 to the first output of the computing system of the simulator 11, and the controls of the simulator 12 are connected to its input.

The optics of a regular ILS, as shown in FIG. 2, includes beam splitters 14 and 15 installed parallel to each other at different heights, a collimator head 16 and a full reflection mirror 18. The subject for the collimator head 16 is, depending on the operating mode, the image plane on the screen a cathode ray tube 19, or a grid plane 17c made on it and highlighted by a digital scale and sighting crosshairs. The plane of the object A intersects the optical axis of the collimator head 16 at the front focus point F, as shown in Fig. 3, therefore, the collimator head 16 ensures a parallel beam path after itself and the operator sees all images of scales, marks, grids, inscriptions, etc. projected onto endlessly remote plane. Since the screen 2 is removed relative to the operator’s eyes at a finite distance, this does not allow the operator to clearly see both the image of the external visual situation on the screen 2 and the information in the exit pupil of the HUD.

If, in the optical system shown in Fig. 3, the minus-a segment is reduced between the optic plane НН 'and the object plane AF, then the beam path after the collimator head instead of the parallel one will become diverging, and the plane in which the direct imaginary image is built

y 'of the object y, will approach the exit pupil of the optics at a finite distance of 1 _p , as shown in Fig. 4.

A similar result can be obtained if we do not reduce the “minus a” segment, but increase the focal length f of the optics, supplementing the collimator head with a scattering lens. For example, in order for the plane of images of scales, marks, marks, etc., visible in the output pupil of the ILS, to be located in the simulator at a distance of 3.73 m from the output pupil of the ILS, it was necessary to supplement the collimator head with a lens of minus 0.28 diopters, as shown in figure 5.

Lens 20 is a negative meniscus with a light diameter of 130 mm and a thickness on the axis of 9.4 mm, has a special shape, is mounted on the outer surface of the frame 22 of the collimator head, centered relative to the frame and, at the same time, is fixed with a bracket 23 with three rubber gaskets.

At the output of a regular ILS, as shown in FIG. 2, two beam-splitters 14 and 15 offset in height (plane-parallel glass plates with a beam-splitting coating) are mounted parallel to one another in order to expand the vertical field of view and materialize the plane in which be the pilot’s eyes when working with the HUD.

When viewing images through a regular ILS in parallel light beams, for example, a grid with an angular height that is high, the upper and lower parts of the image merge for the operator into a single image. But when viewing the same image in diverging beams, which occurs when the collimator head is supplemented with a scattering lens, the upper and lower parts of the previously single image diverge vertically.

In order to eliminate this drawback, as well as to maintain unchanged the location of the line of sight of the HUD relative to the plane passing through the upper boundary of the beam splitter coating of the lower beam splitter 15 and the lower border of the upper beam splitter 14, it is necessary to deviate the lower and upper beam splitters from their normal position by some small angles, making them parallel to each other. The methodology for performing this procedure and the method for calculating the scattering lens constitute the applicants' know-how.

Since the reverse surfaces of the beam splitters 14 and 15 also have reflectivity, when working in diverging light beams, this causes the appearance of a second image lower than the main brightness (flare). To reduce the brightness of glare, an antireflection coating is applied to the back of the beam splitter.

The addition of the collimator head 16 with a scattering lens 20 reduces the lateral increase in the optical system and, therefore, the visible angular dimensions of the images in the exit pupil compared to the standard ones. For example, the addition of a collimator head 16 with a lens minus 0.28 diopters. led to a decrease in the transverse increase of 18.89%. For

Togo. in order to compensate for the decrease in the apparent angular dimensions of the grid 17, the standard ILS grid is replaced by a training one, which differs from the regular linear dimensions. The reduction in the apparent size of the images, the source of which is the cathode ray tube 19, is compensated as follows.

As shown in figure 1, in the inventive utility model used three blocks: character generator 9; a synchronization and switching unit 8 and a low-voltage power supply 7. These are blocks from the standard equipment that ensures the operation of the ILS on board the aircraft, where commands are received at the input of the symbol generator from the on-board digital computer complex (BTsVK), which describe, including , linear dimensions of image elements.

Due to the high cost of the BTsVK and the difficulty of interfacing them with the computer equipment of the simulator, simulators are usually emulated using general purpose electronic computer software included in the simulator’s computer complex. Therefore, it becomes possible to programmatically modify the instructions received at the input of the symbol generator 9 through the interface adapter 12 from the computer complex 11 of the simulator, where a special program emulates the commands of the air-conditioning missile system of the aircraft (unlike the situation when the standard air-conditioning missile system would be included in the computer complex of the simulator the provision of which is hardware-entered in the permanent memory chips, and, as a result, cannot be flexibly changed). Reducing the apparent size of the images can be compensated for by modifying the data fields of those commands supplied to the input of the symbol generator of the HS, in which the linear dimensions of the image elements are described.

The visualization system works as follows. The supply voltage from the on-board power supply simulation system 13 is fed through the low-voltage power supply unit 7 to the first input of the ILS 5, to the input of the symbol generator 9, information from the computer complex 11 of the simulator on the location and numerical filling of labels and scales of ILS 5 is received through the interface adapter 12 specially developed for this purpose , from the output of the symbol generator 9 to the input of the synchronization and switching unit 8, signal control signals of the ILS 5 are received, which are transmitted from the output of the synchronization and switching unit 8 to the second input of the ILS 5. Images reproduced in this case on the screen of the cathode ray tube 19 of the ILS 5 are the subject of an equivalent optical system including a collimator head 16 and a diffuser lens 20 mounted on the frame of the latter and fixed by a bracket 23, as shown in FIG. 5. The relative position of the plane of the subject and the front focus of the equivalent optical system provides the desired location of the plane of the direct imaginary image of the subject

relative to the plane of the exit pupil of the optics shown in Fig.Z when this image is aligned with the plane of the screen 2.

The external visual environment, determined by the position and dynamics of the aircraft and the target in virtual space, simulated by the computer complex 11 of the simulator, is generated by the computer system 4 and is projected onto the screen 2 by the projector 3. Despite the fact that the beam path in the exit pupil of the ILS 5 is not parallel, but the diverging, upper and lower parts of the image, built through the upper and lower beam splitters 14 and 15 of the ILS 5, merge into a single image, since the upper 14 and lower 15 beam splitters of the ILS 5 are deviated from the standard Proposition on some small-angle and not parallel to one another. The adequacy of the size and position in the field of view of the HUD 5 of the grid image ^ is ensured by replacing the standard HUD grid (see Fig. 2) with a training grid that differs from the regular linear dimensions. The adequacy of the size and position in the field of view of the ILS 5 visible images reproduced by the cathode ray tube 19, is ensured as follows.

The commands received in real conditions at the input of the symbol generator from the onboard digital computer complex of the aircraft are emulated in the simulator by a special program in one of the computers of the computer complex 11 of the simulator, while they are modified programmatically in order to compensate for the decrease in the transverse increase in the equivalent optical system " diffusing lens - collimator head "in comparison with the collimator head 16. As a result, flight-navigation and sighting adequate information is reproduced by the operator in a regularly located and having a nominal diameter exit pupil of the optics and the plane of images reproduced through the “indicator on the windshield” is not aligned with infinity, but with the plane of the screen of the visualization system. Thus, the image in the ILS field and outside it is in the same plane and re-accommodation of the operator’s vision when going beyond the boundaries of the ILS field is not required.

The proposed visualization system was implemented during the creation of the simulator of the Ka-50 helicopter and is preparing for preliminary tests as part of the simulator.

Thus, the proposed visualization system can be manufactured and applied in the simulator of an aircraft equipped with a HUD, which allows us to conclude that the utility model meets the criterion of "industrial applicability".

Claims (3)

1. The visualization system of the simulator of a combat aircraft, including a projector and a screen, a computer system for generating images of the external visual environment and a “windshield indicator”, including a cathode ray tube, a grid, a collimator head and two beamsplitters mounted one above the other, characterized in that in the "indicator on the windshield" a diffusing lens is inserted, mounted on top of the frame of the collimator head and fixed on it with a bracket, and part of the lens is cut at an angle to the optical axis, and the upper and lower beam splitters are deviated from the standard position by some small angles so that their planes become non-parallel to one another; in addition, a symbol generator, a synchronization and switching unit and a low-voltage power supply have been introduced, the first input of the “indicator on the windshield” is connected to the output of the low-voltage power supply, the input of which is connected to the simulator's on-board power supply simulation system, the second input of the “indicator on the windshield” is connected with the output of the synchronization and switching unit, the input of which is connected to the output of the symbol generator, with its input connected via an interface adapter to the first output of the simulator computing complex; the second output of the simulator computer complex is connected to the input of the computer system for generating images of the external visual environment, the output of which is connected to a projector projecting an image on the screen, and the outputs of the simulator cabin controls are connected to the input of the simulator computer complex. 2. The visualization system according to claim 1, characterized in that the standard grid is made in the form of a simulator, which differs from the standard linear dimensions. 3. The imaging system according to claim 1, characterized in that antireflection coatings are applied to the back of the beam splitters.