RU2426074C1 - Aerodrome automated flight monitoring, control and demonstration complex of aircrafts - Google Patents

Abstract

FIELD: instrument making.

SUBSTANCE: invention can be used as control device of control automation processes: air traffic control (ATC), aircraft registration (AR), group of targets for increasing takeoff-landing safety, performance of "go-around" and piloting of aircraft in aerodrome zone, during certification, holding of air exhibitions, shows, etc. Complex includes optoelectronic infrared (IR) TV system with wide and narrow bands of view field of cameras for searching, tracking and displaying of aircraft, information recording system; information acquisition, processing, presentation and display systems are located at ATC command station. Transmitters of pulse laser distance-measuring system, precision approach radar, TV system outputs are connected through matching units and computing devices (computers) to information acquisition system made in the form of local computing network with aircraft flight control system interconnected with data transfer system to command station of the appropriate control panels, to real time system.

EFFECT: improving flight safety.

2 cl, 1 dwg

Description

The aerodrome automated complex (AAK) belongs to the field of aviation and can be used as a means of monitoring, video surveillance, recording the flight characteristics of one or several aircraft (LA). The complex is used for automation of air traffic control (ATC) processes, registration of aircraft, a group of targets for air shows at international air shows, certification of aircraft equipment and for monitoring demonstration flights of aircraft.

A known television system for monitoring aircraft landing (see RF patent for utility model No. 82079 dated 11/19/2008) containing at least two television cameras located next to the landing strip and generating video images of the aircraft approaching for landing, a system video block to which are connected television cameras, monitor and video recorder, control unit. Computing devices and additional monitors, each in the number of television cameras, and a network switch integrating computing devices, a system video unit and video recorders into a local computer network are introduced into a television monitoring system in which television systems form a stereo pair, while additional monitors are connected to the outputs computing devices, the first inputs and outputs of which are connected to the system video block, and the second inputs and outputs - to the inputs and outputs of the corresponding blocks government.

In addition, the television monitoring system includes a television camera connected to the system video unit, and a range sensor connected to the network switch.

However, this system does not allow the monitoring of demonstration flights at large and small distances to aircraft, with different levels of atmospheric interference, flights day and night.

The Sazhen-TM quantum-optical system is known, developed by the Scientific Research Institute of Precision Instrumentation, in which the basic technical solutions underlying the design include a rotary support device (OPU), a torque-based behavior system, a computer-control complex, a single time system (SEV), data transmission equipment, weather equipment, laser locator, video theodolite.

The system is designed to obtain external trajectory measurements of rocket and space and aviation equipment by measuring angular coordinates during field tests. The system allows tracking space objects up to 23 thousand kilometers with angular velocities up to 40 angles. s / s, with standard deviations (RMS) of measuring the angular coordinates of point targets 5 ang. s, the maximum angular velocity of tracking targets - 30 ang. deg / s ² , angular acceleration of 150 ang. deg / s ² .

Information channels of the video theodolite - overview and information, form a standard analog black and white television signal; The reporting channel generates a color TV signal in PAL format. The reporting channel with a variable field of view is designed to record the phases of flight of targets and organize reporting in the test process.

The survey channel is used to detect targets by the operator in the auto-tracking circuit of an object to keep it in a narrow field of view.

The measuring channel is designed to measure angular coordinates in the instrumental coordinate system.

The Sazhen-TM system provides search and detection of test objects (OI) in day and night conditions, their automatic tracking with measurement of angular coordinates, range, operational processing and display of the measurement process, the transmission of the obtained data to communication channels in real time.

The system includes:

- car carrier;

- measuring channels: a television channel with a narrow field of view, a color television channel with a variable field of view, an infrared television channel, a laser rangefinder channel;

- slewing ring;

- equipment management, development and registration of information;

- equipment for binding to signals of uniform time (SEV).

However, this system does not allow monitoring of demonstration flights of aircraft at international aerospace showrooms and exhibitions.

A multifunctional optical-location system is known (see RF patent for invention No. 2292566 dated September 15, 2005), which includes optically coupled laser transmitters located on the optical axis of the transmitting channel, which forms a probe laser beam, and a pilot laser that forms a control beam laser radiation, an output telescope, a horizontal platform with first and second mirrors located on it, configured to rotate around a vertical axis, three coaxial rotation shafts, also laid on the optical axis of the receiving channel, the optically conjugated third mirror, the inverse reflective surface of the first mirror, the mirror-lens objective of the receiving telescope, a corner mirror, a combined photodetector, while the second and third mirrors are made with the possibility of synchronous rotation around the horizontal axis, as well as an auto-alignment device including a rectangular prism in the center of the first mirror, rectangular reflective prisms in the centers of the second and third mirrors, a diamond prism with a diaphragm mine installed on the output face of the prism-rhombus, as well as signal processing blocks, drives, current state sensors, control units of the main optical-mechanical units.

The disadvantages of the optical-location system include the following. Although the optical-location system contains a laser locator and a heat direction finder (or radar), however, it does not have multifunctionality and is focused on solving one special problem. It uses a structurally practically unrelated heat generator to obtain data on the azimuth and elevation of the object and a laser locator to determine the range coordinate.

This system does not allow effective monitoring of aircraft demonstration flights, verification and certification of airfield equipment, and landing systems.

The well-known optical-location system IRATS (VV Protopopov, ND Ustinov. Infrared laser location systems, pp. 84-92, M. 1987), adopted as a prototype, designed to track low-flying aerodynamic objects. The system includes a pulsed laser transmitter, an optical laser beam guidance system, a photodetector, a television camera with an automatic tracking system, used as a target designation tool, and a control and data processing system. The television camera searches for objects by pointing its optical axis to a given point in space with the main mirror of the guidance system, which can rotate around the azimuthal and elevation axes, while the television camera can rotate around its axis, compensating for the rotation of the image of the object during azimuth tracking. A pulsed laser transmitter starts an active location mode when an object is detected. The telescope receives a laser pulse reflected from the object and focuses it on the photodetector. Then, at the output of the photodetector, pulsed electrical signals are generated that enter the signal converter connected to the data processing unit, the output of which gives data on the distance to the object. Tracking of the object is carried out by a television automatic system using the drives of the main mirror of the guidance system or by the operator manually.

The optical-mechanical unit is a single structure that carries a laser transmitter, an optical system and a television camera with a periscope that couples it to the optical path. Such a scheme provides the required rigidity and immutability of the adjustment during operation. The base of the entire mechanism is placed on a frame that rests on jacks lowered to the ground, which ensures the necessary stability of the spatial position of the optical system.

However, the combination of television and laser channels in the local IRATS system is difficult, with the need for special measures to ensure the stability of the optical axis of the system, with no control over the invariability of the system alignment during operation. As a result, the accuracy of measurements decreases, and the possibilities of using it in practical work when monitoring demonstration flights of aircraft are limited.

The technical result to which the invention is directed is to increase the efficiency of visual and measuring control over the movement of aircraft along the runway of an aerodrome during takeoff and landing, providing video information about the release of the chassis and mechanisms and control surfaces, the operation and condition of engines , rescue equipment during ejection, automatic search and tracking of aircraft relative to the glide path, determination of flight parameters of the aircraft along the glide path.

In addition, the increase in safety is determined during the landing, take-off, taxiing, demonstration flights, as well as during the development of minima of the aircraft and the pilot, improving the equipment of the airfield and air traffic control system.

To achieve the specified technical result, an aerodrome automated complex for monitoring, controlling and demonstrating aircraft flights, containing systems for collecting, processing, presenting and displaying information associated with information transmission lines with sensors for determining the flight path parameters of aircraft in the areas of the aerodrome, as well as its meteorological conditions, a single time system (SEV), including a pulsed laser rangefinder transmitter, an optical laser beam guidance system a, a television camera with an automatic and manual tracking system for objects, a landing radar station, control panels, an optical-electronic infrared (IR) television system with wide and narrow ranges of the camera’s field of view (EOTS) for searching, tracking and displaying has been added to the complex An aircraft located next to the runway. The information registration system, systems for collecting, processing, presenting and displaying information are located at the command post (KP) of air traffic control (ATC). The complex introduced computing devices - computers, integrated into a local area network. In this case, the transmitters of the pulsed laser rangefinder system, the landing radar station, the outputs of the television system through matching units, computer computing devices are connected to the information collection system made in the form of a local computer network with the flight control system of the aircraft, interconnected with the data transmission system to the CP of the corresponding control panels , with a single time system. Moreover, the radio communication system and the air traffic information display system are also interconnected with the flight control system of the aircraft. In addition, the information collection system is connected through a coordination system with weather sensors. Information about the state of the atmosphere and visibility is used to form processes that affect the quality of the angular measurements of the observed aircraft, which increases the accuracy of the measurements. The information recording system is interconnected with the weather data matching system through a local area network, and the information display system is connected to the terminals of the air traffic information display system and to large viewers screens. Measuring information can be displayed on monitors in real time in the form of numbers or graphs. Registration of video and measurement information can be carried out in real time and used as an objective control. At the same time, a single design, including a PC, television cameras and a laser range finder, is installed on a reference rotary device (OPU). Moreover, the aircraft search and tracking system is based on video theodolites with mirror lenses with the ability to rotate the installation around the three axes of the control system and perform accurate alignment in a single design.

Putting into practice the use of EOTS in the air traffic control modes of aircraft in the areas of aerodromes, air shows and sectors for accommodating spectators during international aerospace showrooms (MAKS) allows you to:

- create an automated external trajectory base of high accuracy with the issuance of measurement and video information about the aircraft in real time;

- transmit, display and register graphic and video information on the air traffic control gearbox during flights and movements of the aircraft in the airfield area in real time;

- monitor and analyze video information about the territories adjacent to the perimeter of the aerodrome, the territory of the air show and the sectors of the placement of spectators during the MAKS and other events;

- conduct training for pilots and test the takeoff and landing characteristics of aircraft during landing under non-standard conditions, participate in international certification of aircraft;

- carry out the measurement of parameters of ejection systems in real conditions while measuring the parameters of the aircraft and the ejected object.

The list of items in the drawing

To clarify the invention, the drawing shows a structural diagram of an aerodrome automated complex, which shows: 1 - aircraft (AC), aircraft (LA); 2-command post (KP) management of air traffic control; 3 - landing radar station (radar); 4 - rotary support device (OPU) measuring angular coordinates; 5 - laser range finder; 5, 6, 7, 8 - a single design of IR, television cameras and a laser rangefinder with an OPU - 4; 6 - a measurement system for a narrow television channel; 7 - a television review system; 8 - channel television IR measurements; 9, 10, 11 - matching blocks; 12 - radio communication system; 13, 14, 15 - computing devices - computers; 16 - terminal control terminal of the air traffic information display system; 17 - aircraft flight control system; 18 - information collection system - local area network (LAN); 19 - a system for coordinating meteorological data; 20 - meteorological observation system; 21 is a display system of air traffic control information; 22 - a system for transmitting data to a command post (CP); 23 - information recording system; 24 - system of uniform time (SEV); 25 - large viewer screens; 26 - runway (runway); 27 - electron-optical system; 28 - television screen; 29 is a screen of measurement information; 30 is a screen of infrared measurements.

The aerodrome automated complex (AAK) includes: information collection and information processing systems - local area network - 18, information presentation and display - 21, connected by transmission lines with sensors for determining the flight path parameters of the aircraft LA 3, 5, 7, 8 in the areas of the aerodrome, and also a weather observation system - 20, terminals of an air traffic information display system with a control panel - 16 at a command post, a single time system (SEV) - 24. Angular coordinate sensor AC - 1 radar - 3, search and tracking system for aircraft - 6, 7, 8 represent optoelectronic infrared television systems (TS) with a variable field of view 7 for search, detection and capture of aircraft and automatic tracking of aircraft and vehicles, 6 - with a narrow field of view for automatic tracking and measurement of angular coordinates of the aircraft. Range sensor to LA - laser rangefinder system 5 - transmitter. These aircraft flight parameters sensors are connected via interface units 9, 10, 11 with computing devices - computers 13, 14, 15 and information collection system 18 - a local computer network connected to the control system - 17 connected to meteorological and weather sensors - 20 and a radio communication system - 12, a data transmission system - 22 to the command post and CEB - 24. This system is based on video teodoliths-telescopes with the ability to rotate installations around 3 rotation axes and perform accurate alignment (rotary support device in OPU - 4).

The device operates as follows

To ensure automatic or manual search, aircraft detection in day and night conditions, automatic tracking with measurement of angular coordinates, range, operational processing, registration and display of aircraft, delivery of received data via communication channels to air traffic control centers, high-precision instruments are used in the aerodrome zone angular measurements.

A significant part of high-precision angular measurements is carried out by a human operator performing visual guidance on the aircraft LA-1, counting the working measure and fixing the measurement results taking into account the parameters and characteristics of the visual and tactile human analyzers. The operator’s task is to eliminate the mismatch between the direction to its geometric center LA - 1 and the optical axis of the sighting device of the television system (TS), the electron-optical system (EOTS). This changes the spatial position of the sighting device - TS, 6, 7, 8 - EOTS using a relative orientation device. The working measure in this case is a dial with divisions - high-precision goniometric devices (UP) with a visual readout of the working measure - theodolites are combined with the TS.

Small angular mismatches, not exceeding the angular field of the sighting device, are eliminated with the help of a compensator, changing the position of the optical element of the compensator and thus shifting the target image in the grid plane, the operator shifts the geometric center of the image with a grid point fixing the position of the optical axis of the sighting device. The spatial position of the sighting device with this method of pointing at the object of measurement of the aircraft does not change.

A working measure is a scale, the division step of which is calculated in accordance with the type of compensator and transmission mechanism, which performs the functions of a relative orientation device. Spatial orientation UP performed using gear and linkage mechanisms.

In an automated (semi-automatic) mode, guidance and tracking of targets is carried out by the operator; The guidance device includes a lens mechanism, an image analyzer and a radiation receiver.

The signal taken from the radiation receiver through the electronic path enters the indicator, according to the testimony of which the operator judges the need for additional exposure through the device of mutual orientation to the spatial position of the guidance device.

Radiation from an object is received by a lens building an image of an object in the plane of analysis. Using the analyzer, the parameters of the optical signal are converted to a form convenient for distinguishing during further development of the angular coordinates of the measured object of the aircraft - 1. The electrical signal captured from the radiation receiver, after conversion in the electronic path, is fed to the electric drive. The latter through the transmission mechanism acts on the mismatch compensator. The compensator changes the direction of the rays in such a way as to reduce the value of the angular mismatch. The compensation process continues until the discrepancy is completely eliminated. The change in the position of the compensator is fixed by the sensor, the output signal of which serves as a measure of the input mismatch.

In the automatic reading of working measures in the control unit after pointing the sighting device at the aircraft object, the operator encodes from the control panel - 16 the necessary information about the measured object and then, with the corresponding command, enables the reading of the working measure. The reading device provides information on the relative position of the sighting device and the working measure. The specified information goes to indicators 28-30, designed for visual perception by operators and to the information recording device - 23. Registration of measured direction measurements is carried out together with the information about the measured object encoded in the control device - 17. The information recorded by the recording device - 23 is processed on a computer - 13, 14, 15.

This measuring system has operating modes - search, tracking and measurement. In the search mode, the aircraft object is ghosted into the angular field of the EOTS 7, 8 guidance device with a certain accuracy, after which the system switches to the measurement mode and accurately determines the direction to the aircraft - 1. EOTS 7, 8 and its transmission to the input of the computer - 18.

The object search operation is performed using the scanning mode of the electro-optical television IR system.

Automation of the process of high-precision angular measurements significantly complicates the design of the observed object LA - 1, which is associated with the need to ensure noise immunity, which is achieved by providing spectral temporal and spatial selection. The circuit of the observed object, in addition to the radiation source, includes a transmitting optical system EOTS 6, 7 (condenser, modulator and lens). The spatial orientation of the transmitting optical system is performed both by a human operator and automatically.

Goniometer system with a transmitting television tube, where the image of an object with a lens is built on a sensitive area of the vehicle’s television tube. The tube is equipped with an electrostatic and magnetic focusing system. Scanning of the electronic image is provided by the horizontal and vertical scanning generator connected to the beam deflection system and synchronized by the reference generator. The video signal from the output of the tube goes to the video amplifier and then to the coordinate measurement unit. Work in the block is synchronized with the work of line and frame scan generators. From the output of the coordinate measuring unit, signals corresponding to the linear position of the measured object on the sensitive area of the tube are output. In this case, one of the coordinates is determined by the position of the video pulse in the scan line, the other - by the serial number of the line. The digital converter converts the indicated time intervals into a sequence of pulses, which is recorded by the registration device - 23 and fed to the computer - 18.

In the process of converting optical and electrical images into a television system, various distortions arise due to the instability and non-linearity of the geometric and electrical parameters of the tube, and inaccurate alignment. In this regard, a calibration channel consisting of a translucent mirror, a lens, an accurate scale and a light source is included in the composition of the television goniometer system. The system is periodically monitored through the channels of the control unit, the scale image is built by the lens on a sensitive area of the tube. The measured parameters of the scale are sent to the storage device, which ensures their comparison with the set, and in case of deviations, corrects the operation mode of the television tube. High noise immunity is ensured by the fact that when the mismatch signal is generated, an insignificant part of the background energy surrounding the measurement object LA - 1 is taken.

The laser rangefinder channel - 5 is intended for measuring the slant range to the test object both equipped with retroreflective reflectors and not equipped (D = 10-20 km). The standard error of the measurements is not more than 0.5 m, the measurement frequency is 50 Hz, the working wavelength is 1.064 μm.

IR channel - 8 is designed to provide, search, detect, track and measure the angular coordinates of targets in the IR wavelength range. The field of view angle is 1 °, the standard deviation (RMS) of measuring the angular coordinates is ~ 10 s, the spectral range of 3-5 microns, the frequency of information retrieval 50-200 Hz.

The support and rotary device OPU - 4 is an azimuthal goniometer device designed to guide measuring instruments and measure angular coordinates. The range of angles of rotation in azimuth ~ 270 ang. hail, in elevation 5-15 angles. hail, maximum angular tracking speed of 30 ang. deg / s, angular acceleration - 70 ang. deg / s ² .

Radar - 3 - radar station, used to determine the location of moving aircraft in airspace. The structure of the radar includes an OPU-4 for automatic measurement of the angular coordinates of targets LA-1.

In meteorological observation system-20, parameters are formed about the state of the atmosphere and visibility on runway-26. Since the atmosphere is the propagation medium of the optical signal, the most important processes affecting the quality of angular measurements in the atmosphere are radiation absorption and scattering, as well as random and regular changes optical characteristics of the atmosphere. Absorption and scattering reduce the level of the signal coming from the observed object to the receiving optical system and thereby reduce the signal-to-noise ratio, which has a noticeable effect on the error in angular measurements.

In a high-precision angular measurement device, accuracy is determined by the influence of atmospheric turbulence and refraction of optical rays. Fluctuations in the phase of light waves in a turbulent atmosphere determine random changes in the angles of arrival of the front of these waves at the entrance pupil of devices 6, 7, 8. Image blur is characterized by the dispersion of jitter, which is determined by the variance of the fluctuation of the coordinates of the center of gravity of the image in a uniform layer of the surface atmosphere. The flickering of the image affects the change in the amplitude of the signals. Range parameter D characterizes the components of the fluctuation of the amplitude of the light wave. The reduction in the photometric characteristics of the image light beam, illumination in the plane of the entrance pupil according to the law of the square of the distance D is taken into account in systems 6, 7, 8.

Refraction is determined by the state of the atmosphere on the measurement path — its stratification, temperature, the presence of clouds and atmospheric fronts, measured by a meteorological observation system 20, 19. One of the main factors determining refraction is a change in the vertical temperature gradient, which is especially noticeable with a change in height above the underlying surface.

In the process of operation, the KP-ATC dispatcher sets the aircraft landing mode from the control panel of the electronic optical system (EOTS). The coordinates of the aircraft - 1, located in the approach zone, arrive at the EOTS 7 and 8 from the landing radar - 3. The EOTS implements an automatic search, capture mode for monitoring and tracking the aircraft from the moment of approach, the movement of the aircraft along the course, glide path, to the moment you touch the runway, move and stop on the runway. The real-time angular information, ranges and visual information in the television and infrared ranges are processed, recorded and transmitted to the ATC - 2. The information received is reflected on the screens of monitors 28-30 and on large screens - 25 viewers.

The aircraft “take-off” mode is also set by the dispatcher on the consoles - 16 KP ATC - 2. EOTS 7, 8 automatically searches for the aircraft on runway - 26 and automatically accompanies the aircraft - 1 from the moment of starting to the moment of loss of its visibility. The received information, both measuring and video information, is displayed on monitors 28-30, 25 and is recorded in the system 23.

In the “taxiing” mode, the EOS, by the operator’s commands at the CP ATC EOTS, enters the manual control mode. Using the EOK control knob, the operator locates the moving aircraft along the runway and switches to automatic tracking mode or can visually view the structures on the territory of the aerodrome.

Claims (2)

1. An aerodrome automated complex for monitoring, controlling and demonstrating aircraft flights, containing systems for collecting, processing, presenting and displaying information associated with information transmission lines with sensors for determining the flight path parameters of aircraft (LA) in the areas of the aerodrome, as well as its meteorological situation, a system single time (SEV), including a pulsed laser rangefinder transmitter, an optical laser beam guidance system, a television camera with an automatic and manual tracking of objects, landing radar station, control panels, characterized in that the complex includes an optoelectronic infrared (IR) television system with wide and narrow ranges of the camera’s field of view for searching, tracking and displaying aircraft located near the take-off landing strip, the complex introduced computing devices integrated into a local area network, while transmitters of a pulsed laser rangefinder system, a landing radar station, TV input-outputs The system through the matching blocks and computing devices of the computer are connected to the inputs of the information collection system made in the form of a local area network, the output of which is connected to the flight control system of the aircraft, as well as interconnected with the data transmission system to the command post of the corresponding control panels, with a single time system , with an information recording system, an air traffic control (ATC) information display system, while the aircraft flight control system is also interconnected with the system for a communication system, an ATC information display system, and the information collection system is connected through a matching system with weather sensors, the information recording system is interconnected with a weather data matching system through a local area network, the information display system is connected to terminals of the ATC information display system and to large viewer screens, while a single design of IR, television cameras and a laser range finder are installed on a reference rotary device (OPU), and information recording systems , collection, processing, presentation and display of information are located at the command post of air traffic control. 2. The aerodrome automated complex for monitoring, control and demonstration of aircraft flights according to claim 1, characterized in that the aircraft search and tracking system is based on video theodolites-telescopes with mirror lenses with the ability to rotate the installation around the three axes of the control gear and carry out accurate adjustments in the form of a single design.