RU10685U1 - LIGHT SIGNALING SYSTEM FOR TAKEOFF AND LANDING FOR LANDING AIRCRAFT AT NIGHT - Google Patents

Abstract

1. The light signal system of the runway for landing at night time for aircraft equipped with landing lights, containing passive reflective landing markers installed on both sides of the runway and oriented with their surfaces in the direction of approach, characterized in that it is equipped with prohibitory markers installed at the end of the runway, reflective shields indicating the "permission of the landing zone" and "unauthorized landing zone", installed one after the other in the alignment among the runway, with the shields made installed so that the front shield of the “clearance landing zone” is located in the direction of landing further inward from the edge of the runway than the second shield, the geometric axis passing through the center of the shields is aligned with the calculated glide path. 2. The system according to claim 1, characterized in that the reflective landing markers are located in the landing zone of the aircraft, made in the form of pyramids, one of the faces of which is oriented in the direction of the aircraft's flight toward landing. The system according to claims 1 and 2, characterized in that it is equipped with additional reflective markers in the form of flat shields located on both sides of the runway on a line perpendicular to it passing through the touchdown point of the aircraft. 4. The system according to claims 1 to 3, characterized in that the front display panel of the landing zones on the reverse side is made with a set of mirror corner reflectors located on a random relief.

Description

The light signal system of the runway for landing aircraft at night.

The invention relates to the field of signaling systems for moving vehicles, in particular to lighting equipment for flight support, lighting equipment as the main and backup means of visual support for landing on the runway (runway), signs of approach to the runway in the dark. It can be used and widely used for landing a fly; p) nhh devices (LA) on field airfields and unequipped landing sites.

There is 1 known landing system for aircraft (helicopters), in which the landing area is limited by mirror triangular (corner) reflectors, and the aircraft contains a searchlight aimed at the runway, and a television transmitting camera with equipment for transmitting the image of the runway to the pilot in the vicinity of the searchlight (headlight)

MKI5 V64 Fl / 18

C 62 a4 1/18

G 05D 1/10 - 12

a cabin, camera mounting and rotation units, filters, display and decoding units of received television images. The aircraft deviates from the glide path in elevation by the position-type light signal. However, this system does not ensure safety of approach since there are no markers to establish the glide path of planning, deviations from which help the pilot navigate during landing; no runway touch points; difficulties in adjusting and aligning mirrors are noted.

Known 2 ship optical landing system, containing the display unit of the landing path of the aircraft, consisting of light sources, blends, filters, a vertical row of Fresnel lenses, and mounted on a stable platform with sensors of angular position, aircraft equipped with a landing light, a three-stage gyroscope associated with the unit indications of a landing trajectory, a collimator sight for pointing at an aircraft and mounted on a mechanical movable unit with an angular position sensor, comprising an optical unit consisting of an translucent reflector, a light source with a reflector, a controlled light filter, a collimator lens, in the focal length of which two transporters are mounted one above the other, fixed in two mechanical nodes of coordinate converters with tracking electromechanical actuators, a landing path display unit based on light-concentrating forms of retroreflective coatings mounted in focus of fresnel lenses.

The disadvantage of this system is the lack of a safety system when the aircraft approaches, because during the regime, the pilot does not perceive the deviations from the landing trajectory — from the course-glide path. The pilot does not see the restriction signals down from the glide path, which is especially important for steep angles of inclination of the descent path and the presence of obstacles in the approach zone to the runway. However, no special directive points are indicated. The visibility range (threshold of recognition of lights) is small, especially in difficult weather conditions (SMU) - (SMOKE).

A known method of visual landing 3, taken as a prototype, the implementation of which in the visual landing system, provides for the presence of passive lights, signs i.e. reflectors directing to the observer (pilot) the light emitted by the aircraft’s onboard landing gears (helicopter). The use of reflectors, the surface of which is coated with highly effective color retroreflective films, creates the necessary color effect, ensures the safety of vehicles in the dark at night.

A disadvantage of the known system is the lack of a specific indicator of the deviation of the aircraft from the calculated glide path when approaching. The visibility of the system lights is small. Lights imply the use of a static mode of operation, and the visual threshold for recognizing optical signals is more sensitive to pulsed ones. In addition, in the absence of horizon visibility at night, the pilot poorly distinguishes deviations from a given course and confuses it with a roll. Dangerous optical illusions appear, the safety of the approach mode is reduced.

The purpose of the invention is the creation of a utility model - improving the safety of an aircraft landing by introducing glide path control by visualizing quantitative indicators of aircraft deviation from the course and glide paths, increasing the range of visibility of system sign lights, eliminating optical illusions at night when approaching.

To solve this problem, in the runway light alarm system for landing at night, aircraft equipped with landing lights containing passive reflective landing markers, in the form of pyramids installed on both sides of the runway and oriented with their surfaces in the direction of approach, it is equipped with forbidden markers, installed at the end of the runway, reflective boards indicating the permission of the landing zone and the unauthorized landing zone, installed one after the other in the alignment and in front of the runway. In this case, the shields are made installed so that the front shield of the landing zone permission is located in the direction of landing farther from the runway edge than the sewing of the unresolved landing zone, the geometric axis passing through the centers of the shields is combined with

calculated glide path. Reflective landing markers located in the aircraft landing zone are made in the form of flat boards oriented in the direction of the aircraft approach and located on both sides of the runway on a line perpendicular to it, passing through the aircraft landing point, and the display board resolved the landing zone from the opposite side with a set of mirror corner reflectors located on a random terrain.

Improving the efficiency of the system in accordance with the invention

It is achieved due to the constructive solution and placement of reflector markers, the color scheme of the installed light locomotive |)

coverage, impulse-flare nature of the reflected optical signals, visualization of the touchdown point (line).

The invention is illustrated by drawings, where in FIG. 1 shows the calculated layout of reflective markers, FIG. 2, 3 shows the kinematic dependences of the aircraft in longitudinal and lateral motion, FIG. 4 shows the characteristics of a reflective coating, FIG. 5 shows the dependence of the light-color sensation thresholds, and FIG. 6 shows thresholds of illumination from background brightness for various color and light signals.

In FIG. 1 are shown:

1 - optical block glide path,

2- green reflective marker (first shield),

3- reflective marker of red color,

4- reflective marker of yellow color, combined in one shield with a red marker,

5- fastening nodes with calibrated force on the boards,

6- aircraft landing

7 - landing light LA

8- runway

9- random relief of mirror corner reflectors,

10-contour markers coated with retroreflective film (pyramids).

in

11 - landing retroreflective markers made in the form of rectangular plate-shields (various colors),

12- barring runway end markers,

13- operator checkpoint,

14- transmitting camera of a television system,

15- image transmission line of a television system,

16- video control device of the television system,

17- transceiver-satellite radio communication with the aircraft.

18- operator,

19- runway touchdown point

20-satellite communication system.

The system contains passive reflective landing markers 10.11 installed on both sides of the runway and oriented with their surfaces in the direction of approach, prohibiting markers 12 installed at the end of runway 8, reflective boards 2,3,4 indicating the permission of the landing zone, unauthorized landing zone installed one after the other in the alignment and in front of runway 8, while the shields 2,3,4 are made so that the shield 2 permit landing zone is located farther from the edge of runway 8 than the shield 3-4 unresolved landing zone. The geometric axis passing through the centers of the shields 2,3-4, combined with the calculated glide path. When the aircraft deviates from the glide path up or down, the pilot sees the upper / lower edges of the shield 3-4 of the unauthorized landing zone located above and below the corresponding edges of the shield 2 of the clearance of the landing zone relative to the geometric axis. The dimensions of the landing permit clearance board are selected so that the optical reflection from the first shield matches the tolerance of the aircraft within the permitted glide path. The dimensions of the second shield are selected so that they are visible to the pilot when the aircraft leaves the tolerances of the allowed glide path. Reflective markers and,

located in the landing zone of the aircraft, made in the form of flat panels, while the rest - in the form of pyramids 10, one of the faces of which is oriented in the direction of the aircraft 6 to land. To indicate the point of touch of the aircraft, the system is equipped with reflective

markers And, located on both sides of the runway-8 on a line perpendicular to it, passing through the touchdown point of 19 aircraft-6. The shield 2 of the solution of the landing zone on the reverse side is made in the form of a set of mirror corner reflectors 9 located on a random relief. The operator 18, located at checkpoint 13, away from the runway, visually controls the LA-6 approach using the screen of the video monitoring device (VKU) 16 connected by a television system (TS) - 14 - 15 image transmission. Image input into TS-15 of the image transfer is carried out using a lens, and output to the VKU-16 screen. If the LA-6 is unacceptably deviating from the calculated glide path, operator 18 notifies the pilot via a 17-20-6 satellite radio communication system and gives a signal ban landing and leaving on the 2nd circle.

Television system (TS) 14-15-16 - a control system for the deviation of the aircraft from a given glide path contains a transmitting uncontrolled television camera 14 with a zoom lens. TS

installed along the longitudinal axis of the runway at the beginning of the strip - in the area of the optical landing point in such a way that its axis is directed along the landing path. The vehicle contains a video monitoring device (VKU-16) and a cable line 15 for communication with a power source. The VKU-16 input is connected via cable line 15 to the output of the transmitting television camera - 14. VKU-16 is located immediately before the approach control operator 18. In front of the lens of the television camera 14, there is a light filter, a diaphragm, a crosshair with a crosshair, a mechanism for changing the focal length associated with the actuator and adjust the brightness.

The operator 18 observes on VKU-16 the image of the approaching aircraft, the deviation of the aircraft-6 from the desired landing path,

marked with a reticule. Operator 18, using a radio communication station, 17 communicates with the aircraft pilot LA-6 and

with

planning. The image of the desired landing path is a crosshair, indicating the glide path and course line. The operator 18 is involved in the analysis of the location and dynamics of the aircraft in space.

With the help of a television system (TS-14-15-16), the LA-6 coordinates are monitored and measured during an approach approach using a given glide path. The vehicle uses a solid-state transmitting camera 14 based on a charge-coupled device, the image on which is supplied using a lens (zoom lens). The coordinates of the LA-6 are measured along the axes that coincide with the direction of personnel and horizontal scanning.

If the image on the screen of the television receiver 16 of the video monitoring device (VKU) turned out to be shifted by an amount X on the horizontal axis and a value Y on the vertical, then with the focal length of the lens f, the image shift by distance X will mean that the aircraft has shifted in the horizontal plane relative to the longitudinal axis the transmitting chamber (tube) at an angle a, which is found from the condition tan a X / f. Similarly, the shift of the image by the value of Y in the vertical plane occurs with a small deviation of the aircraft by an angle p, for which tg p Y / f.

The system provides a visual indication of the position of the LA-6 during the approach with respect to a given glide path and,,, the glide path is determined by the specified position of the optical unit and ensures safe landing on runway 8.

The optical unit 1 consists of individual reflectors - green, yellow, red rectangles of a high-intensity retroreflective film, providing fragility, 5 -7-1 ° in the linear zone ± 0.75 °.

If an aircraft flies along a given glide path of planning, then the pilot sees the pure green color of the rectangle; , (standard glide path angle).

If the aircraft flies higher than the glide path, then it will see a yellow stripe above the other rectangle of the second plan E above the green rectangle: v KIZHE landing, the pilot observes the light picture from a distance to the runway.

The photometric characteristics of the high-intensity retroreflective film are shown in figure 4, which shows

graph of the minimum specific luminous intensity coefficient (cd / lux / m).

A retroreflective surface retains at least 90% of the indicated values if it becomes wet (rain, dew).

To coat markers 2,3,4, a reflective diamond film with prismatic lenses inserted into a transparent coated synthetic resin is used. Film interference filters are used in green, yellow and red shades.

To increase the visibility range of optical markers, impart pseudo-impulse character to optical signals, glare-shield resolution of the landing zone - 2 on the reverse side is made with a set of mirror corner reflectors 9 - film faces located on a random relief. Thus, a reflective glare system of shields 2 and 3-4 is obtained - the effect of re-reflection from the second shield to the back surface of the first and again to the second is used.

Markers 3.2 - flat shield figures with multilayer reflective prygry, on the outer layer of which a film interference optical filter is applied, made with the possibility of transmitting specified color signals, while the reflectors are oriented normal to the path of the light glide path of the aircraft, and their shields are installed at a distance from each other each other by a value of 1, determined by the following relation

1 1/2 logt So / Si (1 + 1 / Lo) 4

where t is the atmospheric light transmittance, SQ is the area of the film coating of the first landing sign, located at the end of the runway closer to the aircraft, S (is the area of the second plan sign, LO is the distance from the first sign to the aircraft; light-signal reflectors are made in the form of markers shields of rectangular shape.

Prohibition markers at the end of the runway 12 are based on the use of the same effect, only the first and second shields are red.

Contour warning lights 10- passive

light-reflecting markers are pyramids and differ structurally. Flat surfaces are used to visualize the touchdown point-line on the runway and the approach to the runway, and the last effect is realized by installing AND markers on the line perpendicular to the runway axis (3-4 on each side of the runway).

Runway contour passive lights consist of 10 markers (markers) set accordingly

near runway-8 with the possibility of visual observation in reflected light of LA-7 headlights. At the same time, markers 10.11 are mounted on racks using cylindrical or spherical hinges -5 with calibrated efforts to tilt the shields in case of unintentional contact of the aircraft with them.

Markers 10 are made in the form of pyramids with a rectangular base. Markers are set so that the line perpendicular to the plane of the marker is directed to the aircraft located on the glide path at the point corresponding to the maximum estimated distance from which the marker is visually detected at night; those. the angles of installation of each i-ro marker are determined by the formulas

a arctg ND ± 5 °, 9i arctg B / C ± 5 °,

where LI is the distance to the projection of the design point of the glide path on the horizontal axis, H is the flight height of the aircraft, B is half the width of the runway.

To ensure the safety of the landing, the fastening racks of the markers 2,3-4 and 10,11 also use brittle racks with articulated spring mounts.

The spectral sensitivity under day conditions is for a light-adapted observer (brightness of at least 10 cd / m) with a field of view of 2 °. For night conditions, it is determined with dark adaptation (brightness no more than 10 °) and a field of view having an angular size

30 °. Those. the relative values of the spectral sensitivity of the visual analyzer, corresponding to vision at different times of the day, are significantly different from each other.

The color threshold of a point source, i.e. the threshold illumination, which is necessary not only for detecting a source, but also for distinguishing its color, is shown in FIG. 5. - the dependence of the threshold illumination (Ezr) of pores on the radiation wavelength A ,, the light and color thresholds of the red light approximately coincide. This means that if the illumination on the pupil is sufficient to detect red light, then this illumination is sufficient to determine its color. With a background brightness of cd / m, the light and color thresholds differ by a factor of 1, for small angular sizes of the observed object the possibility of fixing it is determined by the threshold illumination on the pupil, the minimum value of which is 25x10 lux, 25x10 lux.

Observation of light signals of constant and pulsed action is carried out at any level of background brightness. Therefore, the EQ increases, see FIG. 6. Since the thresholds of light perception are higher than the thresholds of light, at considerable distances color lights are perceived as white and acquire their color as the observer approaches them.

Since red light has the lowest light threshold, it is accepted as prohibitive. For white and red colors, one calculated value of the threshold of illumination is accepted. The calculated thresholds for red and white at night are point N at EQ, for yellow, green and blue, point C at EQ is 10% k, for white during the day, point L at EO (calculated threshold of illumination).

The passive lighting system is based on the use of high-performance retroreflective films of various colors (for example SM-3, DIN ISO 9002 certificate) with the use of noble landing lights, meets the requirements of ICAO.

The indicated visualization system for airfields and the approach to them to ensure flight safety at dusk and at night in conditions of visibility of 2-3 km requires the most insignificant costs for installation and operation.

The system can be used for aerodromes and organization of aircraft landing sites in the Far North, in 1 Ntarktid during the polar night, in emergency areas, remote from settlements, areas where the installation of electrical systems is not possible, and are also equipped as a backup during an emergency power outage Runway.

1. Landing system for helicopters. Application NOS 3629011 Germany, 88.03.10. N / O 03.09.86.

2. Ship optical landing system, a positive decision from 10.25.95 on the application 13.043 173/23 from 08.31.93.

3. A method for constructing passive-type optical systems A.S. No. 292777.

Literature

Claims (4)

1. The light signal system of the runway for landing at night time for aircraft equipped with landing lights, containing passive reflective landing markers installed on both sides of the runway and oriented with their surfaces in the direction of approach, characterized in that it is equipped with prohibitory markers installed at the end of the runway, reflective shields indicating the "permission of the landing zone" and "unauthorized landing zone", installed one after the other in the alignment among runways, with the shields made installed so that the front shield of the "landing zone clearance" is located in the direction of landing further inward from the edge of the runway than the second shield, the geometric axis passing through the center of the shields is aligned with the calculated glide path.  2. The system according to claim 1, characterized in that the reflective landing markers are located in the landing zone of the aircraft, made in the form of pyramids, one of the faces of which is oriented in the direction of the aircraft's flight toward landing.  3. The system according to claims 1 and 2, characterized in that it is equipped with additional reflective markers in the form of flat shields located on both sides of the runway on a line perpendicular to it passing through the touchdown point of the aircraft. 4. The system according to claims 1 to 3, characterized in that the front display panel of the landing zones on the reverse side is made with a set of mirror corner reflectors located on a random relief.