RU2689783C2 - Method and system for long-range radio-electronic reconnaissance based on "track in atmosphere" "radio-insight" object flying in stratosphere with hypersonic speed - Google Patents

Abstract

FIELD: physics.SUBSTANCE: invention relates to reconnaissance in atmosphere of hypersonic target. Disclosed is a method and system for reconnaissance of a hypersonic object by degree of luminosity and radiation temperature of formation of a plasma and a red-hot vortex stream, an albedo of a condensation loop of its "trace in atmosphere", together with geometrical, dynamic and trajectory features of target selection, consisting in arrangement of optimum search conditions by lifting above 21 km on unmanned aeronautical vehicles and synchronous operation of thermal imagers, television cameras, which emit radars for a short time based on the principles of radio-photonics – measuring the range to the ion-electronic "trace in atmosphere" exercise. Their carriers as survey-aiming stations "drift" above ground-based stations for processing information and controlling radio-electronic reconnaissance of the search-tracking complex, where spatial coordinates and parameters of movement of the target are calculated.EFFECT: measurement of angular coordinates by passive optical radiometer and range to target – active radar of meter-high radio waves, calculation of motion parameters with required accuracy.2 cl, 4 dwg

Description

The technical solution relates to the field of registration at a distance of 1045 km from the governing body of the formation of the Aerospace Forces flying in the stratosphere on a hypersound - “radio-invisible” object and determining its location, motion parameters according to the criteria of the disturbed near-Earth air environment called “trace in the atmosphere” - with the accuracy required in practice. For radar control systems and electronic reconnaissance of the Aerospace Forces, the aerodynamic hypersonic target is “radio-invisible” (“radio-invisible”) because the ionized envelope surrounds the physical body in flight in dense atmosphere at a speed of five or more times the Mach number. air that has passed into the plasma state, which shields all radio signals. The timeliness of the reconnaissance of a hypersonic target sets the distance of its detection to 1200-1500 km (depending on speed) - to destroy, with a probability of 0.95, guided missiles of the S-400 anti-aircraft missile system [Kuptsov IM Fighting hypersonic aircraft (HAZL): A new task and requirements for the aerospace defense system (WKO) // Military thought. 2011. №1. Pp. 10-17] and 1045 km (at a target speed of 4500 m / s) for a successful defeat at a distance of 350 km by anti-aircraft missiles of the S-300 V4 anti-aircraft missile system [Smirnov DV, Shuvertkov VV A difficult task, but solvable // Aerospace Defense. 2015. №1. Pp. 32-39].

From the description of the scientific discovery “Effect of Kabanov” registered on 06/26/1957 under No. 1 in the State Register of Discoveries of the USSR with priority from 03/15/1947, a method for long-distance horizon detection of targets in the range of 10–100 m of short radio waves at a distance of 3000 km is known. The author of this discovery is a researcher at the Novosibirsk Electrotechnical Institute NII-16, Professor, Doctor of Technical Sciences N.I. Kabanov discovered the phenomenon (previously unknown) of distant scattered reflection by the Earth of radio signals of the spectrum of decameter electromagnetic oscillations with their return, after reflection from the ionosphere, to the radiation source. The idea was based on the use of the reflection effect of radio waves from the ionized layers of the atmosphere - the height from 70 to 300 km of the ionosphere for trans-horizon detection of a target; that is, taking into account the curvature of the globe with reciprocating sounding, the radar beam will reach the Earth’s landscape at a distance of up to 3000 km. Constructed on the basis of such a process, radars are called single-slide radars. If a longer viewing distance is required, then multi-hop ionospheric radars should be used (two-, three-hop). Radar transmitters emitting at a certain angle to the horizon, radio waves from the ionosphere are reflected and return back. The share of their energy is dissipated by inhomogeneities of the Earth’s surface and spreads in different directions. Scattered radio signals are again reflected from the ionosphere and go back to the Earth, and some of them reach the position of a radio transmitter. Works on trans-horizon radar in the USSR were resumed in 1958 by the winner of the USSR State Prize E.S. Pin. Not knowing about the scientific discovery of N.I. Kabanov, he proposed the method of ionospheric detection at a distance of one aircraft jump on reflective surfaces, at a distance of two jumps (6000 km) of launching ballistic missiles in their high-altitude tracks, plasma trenches. The method envisaged, after detecting the target and tracking with the accuracy achieved by the decameter radar, providing information to the radar of a range of less long waves with a higher resolution when the object reached its reconnaissance field. The survey and observation functions are divided between radars operating in different zones. However, the validity of the operation of the over-the-horizon radar is associated with difficulties due to the unexplored ionosphere in the North Pole (Polar Cap) region. The structure of the ionosphere and density maxima in the mesosphere, mesopause and thermosphere strongly depend on the phase of the solar activity cycle, the season, the period of the day, the geographical position (the polar zone and the auroral oval of the Arctic, the equatorial and midlatitude zones) and the disturbances caused by solar activity (including including northern or northern lights - English. "aurora borealis"). Due to the solar radiation in the X-ray and ultraviolet range of the electromagnetic spectrum and the corpuscular solar flux, the main part of ionization increases on the illuminated side of the globe and decreases on the shadow one. For a priori estimates of the state of the route of the decameter signals of the ionospheric radar, special space (orbiter) devices and ocean (sea) ships are required, giving recommendations on the assignment of the operation mode of the over-the-horizon radar, duration and frequency of emissions. In addition, the American complex of energy electron pumping of ground-level gaseous atmosphere (“warming up” of atmospheric plasma) of a research project called “studying the ionosphere and auroras” using high-frequency radioelectronic emitters will have a negative impact on the operation of radars of the over-the-horizon review. Such systems of ionospheric research, antenna fields and special radars are located on the Spitsbergen archipelago "SPEAR" (Space Plasma Exploration by Active Radar) in the Arctic Ocean, in Norway "EISCAT" (European Incoherent Scatter Radar site), on the islands of Greenland, Bermuda and Puerto Rico, Alaska "HAARP" (High Frequency Active Auroral Research Program) and "HIPAS" (High Power Auroral Stimulation), in Australia, in Peru, on "Sea-Based X-Band Radar" floating platforms. The complex of energy electron pumping of the atmosphere with its super-power radiation heats the surface gas layer (ionosphere) filled with ionized atoms or electric particles with ions up to 1600 ° C and more, which leads to the formation of an artificial ion cloud (tens of kilometers in diameter of a plasmoid formation more powerful than a million northern lights times) with a highly energetic state of atoms. High-frequency "warm-ups" of the ionosphere can be performed simultaneously from forming the pumping circuit over the whole of Eurasia (including Russia) three positions (Alaska - Greenland - Norway), which means the ability of such a complex to form artificial ion formations and formations in any region over the Northern Hemisphere of the Earth purposefully move them, creating intentional interference in the course of target detection by trans-horizon (ionospheric) radars. There is a method of exploration of aerodynamic aircraft with low radar visibility (including high-altitude), patented in the United States as "Method of detecting a moving target using background radiation" or "Radar of a new generation" A.N. Anuashvili, with a background principle of data acquisition. The authors of the scientific discovery made at the Institute of Control Sciences of the Russian Academy of Sciences "Pattern of manifestation of the mobility of an object" (Diploma No. 55 of 05/30/1997 based on the resolution of the Department of MMPU RAS No. 10 of 02/22/1992) AN Anash. and Maklakov V.V., and academician Prangishvili I.V. claim that in flight the object "invisible" inevitably leaves a "trace in the atmosphere", and it is precisely him that the radar can detect. The invention of A.N. Anuashvili concluded that if the probing radio waves of the generator are directed to the background (ionosphere), then the secondary waves reflected from it create oscillations that are consistent with the primary signals. The coherent flow of oscillatory processes or harmony is disturbed when an aircraft “stelts” -apparatus appears in the field of radio waves, which serves as a detection signal. Oscillations from the secondary generator (background) in the phase mixer of the receiver detection device are mixed with the radiation of the primary generator, and a coherent component is selected, indicating the degree of harmony (consistency) of the oscillatory processes of the primary and secondary generators. If there are no moving objects in the field of view, then the coherence is maximum. In the case of the appearance of a moving object in the field of passage of radio waves, harmony falls (is violated) according to a certain law. The violation of coherence (consistency) does not depend on the degree of "visibility" of the moving target. An invisible object does not change the amplitude of the signals, but changes their phase during movement, therefore it is possible to detect a target with low radar visibility (“radio transparent”) and the so-called “phase” object (see US Pat. No. 6,707,488, dated March 8, 2004, priority from 04.05.1999). The disadvantage of this method is the "stationarity" of the radar and the requirement to use a primary radio wave generator sensing its position using its own signals. This allows the opposing side to conduct reconnaissance and organize jamming or fire suppression of such active radars at the planning stage of the strike.

The closest analogue to the proposed method and intelligence system of the target, "radio-invisible" because of the ionized plasma membrane on hypersound, adopted outlined in the patent of the Russian Federation on 10.10.2012, No. 2536769 "Method and system for far optical detection and positioning flying in the stratosphere or large altitude with the supersonic velocity of the object according to the criteria of the condensation wake of its power plant in the atmosphere "IPC G01S 5/00. The idea is based on the regularity of the formation of vapor from the near-earth gas environment and emissions from an engine flying at an altitude of more than 7 ... 9 km of an extended and contrasting aircraft against the cloudless sky of a condensation plume emitted using a multispectral optical radiometer at a distance of 350 km. The location of the aircraft determines the coordinates of the front cut of its “trace in the atmosphere”, and the “technical” view is placed on board an unmanned helicopter patrolling above the terrestrial landscape by 3 ... 3.5 km. The criteria for detecting a condensation plume of a power plant flying in the stratosphere, or at a high altitude with the supersonic speed of the object are: the value of the reflection coefficient of solar radiation by the target surface - albedo; form in the form of streaks or stripes (ribbons) against a cloudless sky; exceeding the Mach number 1.2 times or more, the speed of movement of the front of an artificial cloud of the upper tier of the pinch-cumulus “road” type (condensation plume). The very system of long-distance optical recording and determining the location of an object flying in the stratosphere or at high altitude with supersonic speeds according to the signs of a condensation trail of its propulsion system in the atmosphere is a mobile goniometric complex from a set of interconnected radio links of data exchange of the ground guidance point and three or four observation-sighting aerial posts with positions and a base (hypotenuse) located along the vertices of a rectangular isosceles triangle, orienting my perpendicular to the line of sight of the target. That is, the combat use of the reconnaissance system limits the meteorological conditions and the duration of patrols of robotic helicopters. The disadvantages of the prototype is the dependence of the detection distance on the distance of direct vision in the segment of wavelengths from 12 nm to 1.0 mm of the spectrum of electromagnetic radiation. For example, if a reconnaissance object moves above sea level at an altitude of 40 km, then, according to the optical horizon distance formula [Zvereva S.V. In the world of sunshine. L .: Gidrometeoizdat, 1988]:

D _OG [km] = 3,82 × {(N _OR [m]) ^0.5 + (N _KSh [m]) ^0.5 }, where H _OR = 3500 m and H _KS = 40000 m;

the registration mark of a target of a known type will not exceed 990 km, when the required distance is at least 1045 km. At the same time, photon fluxes reflected from the surface of an object of exploration will pass to the means of "technical" vision directly above the earth's surface in the "opaque" layers of the lower troposphere, where absorption and scattering by atmospheric components, natural meteorological formations and particles of artificial solar aerosols dominate. radiation.

The objective of the proposed technical solution is the implementation of a long-range, at least 1045 km, radio-electronic reconnaissance of a “point” (at this distance) object flying at heights of the stratosphere from 50-55 km to 25-30 km with a hypersonic speed greater than Mach number five and more than once - “radio-invisible”, in the plasma shell - “radio-invisible” means of aerospace attack, for example, a cruise missile (single-launch unmanned aircraft machine), guided gliding combat unit (glider) of the “HGB” type, - detecting and measuring angles x coordinates of the target with a thermal imaging camera and television cameras, ranging with an active radar meter radio waves and determining its motion parameters with the accuracy required in practice to provide information on fire effects at altitudes of 25 ... 35 km of anti-aircraft missile systems with thrust vector control and 350 km affected area.

Section II, “Military Hazards and Military Threats of the Russian Federation”, edited by the Military Doctrine of the Russian Federation, approved by the Security Council of the Russian Federation on December 19, 2014, and approved by the President of the Russian Federation on December 25, 2014, highlights the intentions of the US Air Force to deploy strategic non-nuclear weapons of high precision in space and the implementation of the concept of the “Ordinary Immediate Global Impact”, which represent this threat to the weapons system are listed in paragraph 15. “The characteristic features and characteristics of modern military s conflict "- is: the use of comparable effectiveness with nuclear warheads weapons based on new physical principles, precision hypersonic mass scale, electronic warfare systems, controlled unmanned aerial vehicles and autonomous maritime, robotic models of arms and military equipment and information management systems.

The prototype of the orbital system of a strategic high-precision conventional weapon is the Kh-37 V robotized aerospace vehicle, maneuvering at a height of 100 to 70 km at a hypersonic speed when diving from the space environment to the Earth’s atmosphere. At the conference dedicated to the 100th anniversary of the Air Defense Forces of Russia (December 8, 2014), P. Sozinov, General Designer of the Almaz-Antey Concern, noted that today inter-medium, capable of maneuvering into the homosphere for low-profile weapons using a low orbit the Kh-37B aircraft allows you to put into space and, after passing through missile attack warning systems and other reconnaissance equipment using orbital parameters, deliver up to three guided planning units to the target [K. Yu. Russia - USA: opposition increases // Russian Bulletin. 2014. No. 26 of December 29]. Modern domestic firing anti-aircraft missile systems and promising new ones do not have the ability to successfully intercept X-37B-type aerospace platforms maneuvering from more than 7,500 m / s speed in the corridor of altitudes from 100 to 70 km above the earth's surface. A hypersonic aircraft, in accordance with the concept of the Military Encyclopedic Dictionary, is capable of flying in space and the atmosphere with a fivefold Mach-Mayevsky speed and faster and maneuvering using an aerodynamic force plane (rocket). In addition, sustained hypersound movement in a dense near-earth gas environment is possible only with a sixfold excess of Mach number by the speed of the aircraft, and flight using aerodynamic forces, with the ability to maneuver, is in a safe altitude corridor above sea level, the upper and lower thresholds of which limits the density the atmosphere (the maximum requirement for ensuring the lift of the airframe is below 55 ... 70 km; the smallest is the condition to prevent the structure from overheating - 20 ... 25 km above the earth's surface). The maximum limit of the safe or correct altitude range for aircraft with hypersonic ramjet engine (35 ... 50 km) limits the need for a natural oxidant - air (oxygen) flow sufficient for its operation. When a near-Earth dense gaseous medium breaks through a hypersound physical object, the intensity of the aerodynamic heating of its body, due to friction about its components, is proportional to the product of the density of the atmosphere and the velocity emitted to the third power. That is, an aerodynamic aircraft, moving faster than the speed of sound five or more times in dense layers of the surface atmosphere, is not a man-made aircraft machine, but an artificial meteorite. To date, there are no serial models of hypersonic combat aircraft, and their development in the United States is conducted in three main areas: the non-motorized maneuvering warheads of submarines or sea-based ballistic missiles; hypersonic airborne cruise missiles; land-based and sea-based missile planning systems. Equipping ballistic missiles with maneuvering, conventional-type guided planning blocks is the cheapest and easiest way to create hypersonic weapons. A group of robotized aerospace planes capable of staying in space for several years (prototype X-37B) armed with guided non-powered shells (prototype HGB) planning to hypersound more than 3,500 km in the shortest a term of strategic objectives, provides the opportunity for the US Air Force to strike first and defeat a global armed conflict.

Maneuvering non-motorized bomb "HGB" (short for "Hypersonic Glide Body", eng. "Hypersonic glider"), "intra-atmospheric", as defined by the US National Research Committee, as a component of the AHW rocket-planning combined system (short from "Advanced Hypersonic Weapon", English "progressive hypersonic weapon"), is a guided planning combat unit, launched by a carrier above the earth's surface at 130 km (into the "near" space), from where it dives, to get additional kinetic energy, into the atmosphere Earth to a height It is about 45 km above sea level, after which it performs cabing with a rise in a safe (up to 50 ... 55 km) high-altitude corridor and then gradually decreases for about 35 minutes (between the vector of its speed and the local horizontal, the angle θ << 0.1 rad. ) to the object of attack with an average speed of 2600-2900 m / s, and directly in front of it from a height of 30-35 km above the Earth's landscape almost vertically falls on it with up to 10 m accuracy of destruction. At the same time, at a distance of about 2500 km from the launch point, after 7.5 minutes from the moment of launch, at a speed of about 3200 m / s, equilibrium stable movement mode is established on the HGB hypersound and, after overcoming 3800 km, its speed drops to 1000 m / s [James M. Acton. Hypersonic Boost-Glide Weapons / Science and Global Security. 2015. Volume 23]. The provisions of the project "AHW" Flight-1A "" and the characteristics of the apparatus "HGB" are classified, and information about the real profile of its flight can be taken from [Alan R. Shaffer. Science and Technology Priorities And Hypersonics / AIAA Speakers Day Space Transportation TC. 2012. March 8] and [Graham Warwick. Hypersonic X-Plane (HP) - DARPA Tries Again / Aviation Week & Space Technology. 2012. August 26].

Planned for 2018 ... 2020, the adoption by the US Army of the AHW "Flight-1A" rocket-planning systems, 2019 ... 2020 - of the X-37B robotic aerospace aircraft and by 2023 ... 2025 ( due to the difficulties of developing a reliable hypersonic ramjet) - single-launch combat aircraft. Movement in a dense atmosphere of an aerodynamic aircraft on a hypersound causes the phenomenon of "plasma flow" (because its speed is not less than five times the Mach number - this is the border in the area of which the physical properties of the air flow change: in the boundary layer near its surface ionized and receive an electric charge), and extreme temperatures are observed in the nasal (about 2200 K) and bottom flow regions (of the order of 1500 K). A trail of considerable size in space (heated by a vortex flow), heated to 1000 K, appears. Also, reflecting meter (“very high frequency”) and decameter (30–70 MHz) radio waves, having the form of a “cylindrical tube” ion-electron trench, are also formed and gradually expanded. The effect of hypersonic movement of an object in a plasma envelope in a dense gas surface environment will cause the formation of an extended contrasting background of a condensation plume with a skyline of 54-56 thousand meters above sea level [Meteorite Chelyabinsk is a year on Earth. Materials of the All-Russian Scientific Conference / [Editorial: N.A. Antipin and others; composition. ON. Antipin]. Chelyabinsk: Stone Belt, 2014].

That is, the "trace in the atmosphere" of an aerodynamic object flying through hypersound in a dense near-earth air environment is a combination of plasma formation, red-hot vortex flow, condensation plume and ion-electron

along with a continuum of criteria: geometric (shape in the form of a strip - tape), dynamic (speed of movement of the front - front cut-off five times or more exceeding the Mach number) and trajectory (between the vector of its speed and the local horizontal angle θ < <0.1 happy.).

The task of electronic intelligence of a “radio-invisible” object moving in the stratosphere with a hypersonic speed at the turn of 1045 km according to the signs of its “trace in the atmosphere” is solved in the proposed technical implementation due to the fact that the real-world numerical components of the physical body in space: its illumination, its own thermal and brightness luminosity and background, its size and color (primary brightness contrast with the sky), its temperature (true thermal contrast with the surrounding background), optical transparency of the layer of the environment of gases in the path of photon fluxes between the observation system and the target (over the five-kilometer "lower" region of the troposphere, where there is no aerosol scattering of the energy of photons by the components of the atmosphere) "technical" vision (performance indicators - quantum efficiency, the minimum allowable temperature difference of the photodetector of the camera's photodetector, thermal imager respectively). The idea of the optimal solution of the problem lies in the selection of the infrared infrared imager (3.0 ... 5.0 microns), visible cameras (0.38 ... 0.76 microns) and near infrared (0.76 ... 1.1 microns) spectral channels of the optical radiometer , with photodetectors based on large-format “arrays in the focal plane” of the lens (FPA - “focal plane array”) of high sensitivity, not “pinpoint” at a distance of 1045 km of the body surrounded by plasma layers of the “radio-inconspicuous” object, but visible at a long distance by systems radio electronic oh, radar) reconnaissance of the contrast over the background of the firmament, extended “trace in the atmosphere” and organization by installing a thermal imager, cameras and measuring the distance to the radar target on the principles of radio photonics on the sides of unmanned aerial vehicles, airships - close to the ideal conditions for registering an object. The criteria for detecting a "trace in the atmosphere" of an object moving on a hypersound in a continuous atmosphere are: thermal contrast of the sky (background) with a plasma formation and a heated vortex flow (difference of their radiation temperatures), brightness contrast of the plasma formation and a condensation plume with a background (difference of their luminous intensities - luminosity luminosities and parameters of solar radiation reflection - albedo, respectively); shape in the form of a strip - tape; exceeding the Mach number five or more times the speed of movement of the front, front cutoff; θ << 0.1 rad. angle of its vector to the local horizontal. Taking into account 10% of the heat transfer index, the thermal field of the tangling shell near the surface of an object flying on a hypersound in a continuous atmosphere can be an order of magnitude hotter than heating the case and near the nose can exceed 10000ºС [Tambovtsev VI, Shevyakov IA, Litvinov A .BUT. Radio transparency of the ionized shell that forms around a hypersonic object in the mesosphere. Bulletin of the University. Chelyabinsk: Ural State University, 2015. Vol. 15, No. 3]. Natural electromagnetic waves continuously absorbed and emitted by any body with higher than absolute zero — minus 273.16 ° C — temperature — thermal radiation whose total energy (proportional to the temperature raised to the fourth power) rises as the heat increases in the spectrum of the short infrared waves. The temperature of the surface of the Sun, when comparing its emissivity with an absolutely black body, corresponds to 5900 K, the temperature of an absolutely black matter. Heated to 2500 K, the physical body emits optical waves with a length of 0.56-0.76 microns, or light radiation of red, orange, yellow shades. The movement of plasma formation and the eddy current heated to 1000 K in the surface air environment will cause its gas components, including water vapor, to warm up and the atmospheric moisture, not having time to evaporate, will cool (due to thermal radiation and turbulence to ambient temperature). When its temperature is below minus 30 ... minus 40 ° C (according to GOST 4401-81 "Atmosphere standard. Parameters", in the altitude range from 25 to 37 km above sea level), atmospheric moisture and water vapor sublimate - bypassing the liquid phase, go into ice microcrystal s, if this temperature is in the range of minus 10 to minus 30 ° C (in the present problem, in a train of altitudes from 37 to 55 km), then microscopic water droplets condense or turn into microscopic water droplets. water droplets creates the refraction of solar radiation (light) and makes visible a condensation plume (eng. "contrail", "condensation trail") "of a trace in the atmosphere" of an object flying on a hypersound for some time. Hypersonic is the speed, five times and more exceeding the Mach number — a dimensionless, numerical value equal to the ratio of the speed of the moving matter to the local (varying with altitude) speed of sound. The speed of propagation in the atmosphere of sound determines the product of the number 20.046 and the square root of temperature — in degrees on the Kelvin scale — the near-earth gas environment at a given height. In the altitude range from 25 ... 30 km to 50 ... 55 km above sea level, the variation of the standard atmosphere temperature is as follows: 221.65 K and 226.51 K - at altitudes of 25 km and 30 km, then increases to 270.65 ° K - above the earth's surface by 47 km and up to 51.4 km remains unchanged, after which it decreases, and is 260.77 K higher by 55 km of the earth’s landscape. Therefore, the Mach number will vary: from 298.5 m / s and 301.7 m / s - acceleration to about 329.8 m / s value, and to 323.7 m / s, a subsequent decrease, respectively, or the threshold values of steady hypersonic flight : 1791 m / s and 1810 m / s, with an increase to about 1979 m / s and a further decrease to 1942 m / s, respectively. These values give the right to introduce a dynamic decisive criterion for the allocation of a "trace in the atmosphere" of an object flying on a hypersound - the speed of movement of the plasma formation front and the front section of the condensation loop faster than 1700 m / s. At the same time, the errors of the "technical" view of measuring the angular coordinates of the "wake in the atmosphere" front depend on the resolution of the two-dimensional photodetector array of the photo-receiver of optical radiation emitted by its discontinuity topology (size and number of elements). A thermal imager and telecameras of an optical radiometer have the ability to accurately coordinate the angles of the front sections of plasma formation and condensation plume, respectively, but cannot measure the distance to them. Therefore, the optical radiometer of an unmanned aeronautical device, determining the azimuth and elevation of the target object by spectral channels, generates and provides target indication to the on-board radar on the principles of radiophotonics from 4 to 6 m wavelength of radio oscillations for measurement with sufficient (for anti-missile control with an active radar homing head) range accuracy to ion-electron sim. Consequently, the proposed system of long-range radio-electronic reconnaissance at a height of 25 ... 55 km above the terrestrial landscape (stratosphere) of a “radio-invisible” object flying on a hypersound, according to the signs of its “trace in the atmosphere”, is a search-tracking complex consisting of interconnected radio links of data exchange of three four ground information processing and control points (one of which is the reference) and three or four geostationary observation and sighting posts located above them (unmanned aerial oplavatelnyh devices -motorizovannyh airships) stratospheric home. The technical solution allows the detection and measurement of location angles of a “trace in the atmosphere” of a “radio-invisible” object flying at hypersonic speed in the stratosphere in a passive mode, without radiation, and determining the distance to it using active radar, thus performing spatial accuracy with practical accuracy. coordinate measurement and trajectory tracking of the target The method and system of long-range radio-electronic reconnaissance flying on a hypersound in the layers of a dense gaseous environment of a “radio-invisible” object according to the signs of its “trace in the atmosphere” consist in receiving three (or more) onboard optical radiometers of unmanned aeronautical vehicles (airships) spaced by the given (to 200 km) distance in space by the positions emitted by a plasma formation and a hot vortex flow - heat waves emitted by a plasma formation - light radiation, and the sun's rays reflected surface of the condensation plume. The level of brightness luminosity and the radiation temperature of the plasma envelope around the hypersonic object and the sun reflectance indicator (or albedo) of the condensation plume and the radiation temperature of the incandescent vortex flow, “trace in the atmosphere” technical criteria, are in the continuum with a geometric shape (strip shape is tape), trajectory (between the local horizontal and the velocity vector of the front cut of the "trace in the atmosphere" angle θ << 0.1 rad.), dynamic (the speed of movement of the plasma formation front and condensation Foot Loop exceeding Mach number of five or more times) crucial features greatly increases the probability of detecting scouting targets. Thermal (brightness) contrast "trace in the atmosphere" against the background of the sky is used to determine and calculate the angular coordinates of the object and the parameters of its movement. Radar photonic radar measures the slant range to the ion-electron simulator of the target. The numerical value of the distance and the numerical values of the elevation angle and azimuth of the "trace in the atmosphere" front determined by the spectral channels of the optical radiometer - with photodetectors with detailed resolution - based on photodetectors equipped with large format arrays - find the spatial coordinates of the location of the object being explored - using algorithmic procedures. The altitude of the target above sea level is calculated as a function of the slant range to the "trace in the atmosphere", the elevation angle of its front section and the radius of the Earth, the target velocity is equal to the calculated moving speed of the plasma formation front in the near-earth gas environment. The motion vector — the value of the course — of the object of intelligence is considered to be equal to the average value of the displacement vectors of the fronts of the condensation plume and the front cut of the hot vortex flow. To clarify the technical solutions presented graphic documents. FIG. 1 shows a block diagram of a system of long-range radio-electronic reconnaissance of a “radio-invisible” object flying at hypersonic speed in the stratosphere, according to signs of a “trace in the atmosphere”; in fig. 2 is a functional diagram of a three-channel optical radiometer for isolating a light-emitting plasma formation ("cocoon") and a light-reflecting condensation plume (CS), as well as heat-emitting plasma clouds and red-hot vortex flow (RTD); in fig. 3 - characteristics of the arrays of photodetectors MFPU-S, ELCM 1075, ELCM 1077 photodetectors of the thermal imager and TV cameras S3C / 075 and S3C / 077, respectively; in fig. 4 shows the dependence of the quantum efficiency of the ELCM 1075 and ELCM 1077 matrices on the wavelength of sunlight. The technical solution of the method and system of long-range radio-electronic reconnaissance based on the signs of “trace in the atmosphere” of a “radio-invisible” object flying in hypersonic speed as follows. The infrared signals emitted by the plasma shell of the object being sighted and its whirling vortex are recorded by MFPU-S arrays of thermal image forming two-dimensional images (sensitivity range 3 ... 5 μm; format 512 × 640 pixels of size 25 × 25 μm; equivalent to noise allowed temperature difference up to 25 mK) - Instruments of the Institute of Semiconductor Physics. A.V. Rzhanov of the Siberian Branch of the Russian Academy of Sciences (Novosibirsk) of digital photodetectors of thermal imagers, light radiation and sunlight emitted by a plasma formation reflected by a condensation loop are received by the ELCM 1075 matrix of panoramas creating visual panoramas (operating range 0.145 ... 1.0 μm; format 1225 × 1300 elements size 14 × 14 μm; quantum efficiency 0.57 in the 400… 750 nm optical spectrum) digital photodetectors S3C (S3C / 075) and ELCM 1077 (working range 0.145… 1.0 μm; dimension 1040 × 1160 pixels with an area 16 × 16 um; quantum efficiency The awn 0.4 in the area 750 ... 900 nm optical waves) photodetectors of the type S3C (S3C / 077) - by the blocks of the group of companies "SILAR-ELAR" (St. Petersburg) cameras (see Fig. 3 and 4), which are placed as a target load on the boards "drifting" above sea level in the height range of "wind- (bicycle-) pauses" (in geostationary mode) unmanned aerial vehicles or motorized stratostats - airships of the Berkut type (1000 kg payload; the cruising level of the soaring heights above the Earth’s landscape is 20 ... 22 km with preservation of a constant geographical position; up to 120 days - the temporary duration of the "hovering"; shell size: diameter - 51 m; length - 250 m and volume - 320 thousand cubic meters. m) Avgur - Balloon Systems Corporation (Moscow), while unmanned aeronautic vehicles patrol over ground information processing and control points. A set of interconnected executors (target detection and range measurement operators) and automation equipment of the ground information processing and control station (electronic intelligence stations) as part of the payload data exchange modules of a motorized stratostat with a system central computer, information receiving and transmitting devices with neighboring and higher control bodies , mapper of display programs and ergonomic workplaces, interacting with onboard equipment of the airship of the type “Berkut "Which converts the received analog radiation of optical images into bit signals, the accumulation and delivery to the consumer via the radio line of data exchange of panoramas of the survey (in digital form) and message patterns - this is an automated control system for combat use in the search and tracking complex of a detachment of sight-sight posts ( OPP) electronic intelligence. The block diagram of the system of long-range radio-electronic reconnaissance flying in the stratosphere on a hypersound aerospace object according to the signs of its "trace in the atmosphere" as a search-tracking complex consisting of: ground information processing and control points (POI and U) and geostationary motorized stratostats, unmanned aeronautical vehicles as surveillance and sighting posts (OPP), is depicted in FIG. one.

The choice of a luminous plasma formation as an exploration object is based on the following. To calculate the range of vision of lights, the Allard's law (squares of distances) is used - an expression relating the illumination E _v created on a plane located at a distance S _n perpendicular to the line of sight in the atmosphere with transparency τ _atm . (Λ _EMI ) or attenuation σ _aus ( λ _EMI ) "point-like" light source with I _v intensity, - in formula form [Guidelines for determining the range of visibility on the runway (RVR). RD 52.21.680-2006. M .: ANO “Meteoagency of Roshydromet”, 2006]:

;

;

- представленная в энергетических единицах измерения облученность на срезе объектива телекамеры;

- угол между направлением потока света и нормалью к облучаемой поверхности; λ_ЭМИ ^- средняя длина волны излучения.where E _v is the illuminance expressed in photometric values of measurement;

- the irradiance presented in the energy units of measurement at the camera lens cut;

- the angle between the direction of light flow and the normal to the irradiated surface; λ _EMR ^{- the} average wavelength of radiation.

The intensity of glowing hot to 5780 ... 5900 ° K of an absolutely black body (Sun) is 3 × 10 ²⁷ cd; the intensity of the glow of absolutely black matter heated to 2000 ° C (the SAB-250-200 lighting bomb) is about 1.02 × 10 ⁷ cd; Taking into account the definition adopted at the XXVI General Conference on Measures and Weights in 1979: candela - luminous intensity in this direction from the intensity of radiation at a frequency of 540 × 10 ¹² Hz equal to 1/683 W in solid angle one steradian of monochromatic radiation source , the light intensity of the formation of a plasma with a temperature of 2500 ° K with a sufficient accuracy for calculations can be assumed to be 2 × 10 ⁸ W.

It makes sense to consider the procedure for determining the transmittance of atmospheric optical radiation τ _atm . (Λ _EMP ) in more detail. The use of the atmosphere “drifting” in the altitude corridor “velopause” (above the Earth’s landscape at 21.33 km wind speed is not more than 10 km / h) of an unmanned aeronautical vehicle - carrier of radio electronic reconnaissance station, along with the most realizable geostationary flight mode; the curvature of the Earth at a given line of detection of a target moving at an altitude of 40 km above sea level (according to the formula for the distance of the optical horizon, the distance of direct vision is about 1322 km) and the effect of aerosol scattering Ia photon energy in the "bottom" of five kilometers troposphere on scouting process registration object (air environment as close as possible to the ideal - dustless, but containing water vapor at heights greater than 5 km above the earth's surface). In the case of registration by means of electronic intelligence at the turn of 1045 km of an object flying to the stratosphere of the stratosphere of the stratosphere, the path of photon fluxes between its wake in the atmosphere and the optical radiometer will pass, according to the cosine theorem 6,371 km of the Earth’s average radius, 8,288 km above its landscape. In the present example, a layer of optically inhomogeneous atmosphere on an inclined 1045 km long path is represented by two layers of 636.8723 km in length between the target and the point of closest approach of the photon flux path to the Earth’s surface and 408.1277 km between this point and the reconnaissance means, and during propagation over the five-kilometer-long "lower" region of the photon troposphere, the weakening of their energy by the components of the near-Earth gas medium is due to only molecular scattering, since the phenomenon of aerosol scattering is absent. At altitudes of 21.33 km, the location of the observation means, 40 km of the location of the object being explored and 8.288 km of the point of greatest approximation of the photon flux path to the earth's surface is the average value of the molecular scattering index, according to the ratio [Rec. ITU-R R. 1817 Recommendation ITU-R P.1817 * “Propagation data required for the development of ground-based optical links for communication in free space” (Question ITU-R 228/3, 2007):

=1013 мбар; Р_А-атмосферное давление на высоте h над ландшафтом Земли; Т₀=273,15 К; Т- атмосферная температура на высоте h над земной поверхностью; λ [мкм] -длина волны радиации; ГОСТ 4401-81 «Атмосфера стандартная. Параметры» приводит: на высоте 21,35 км Т=217,929 К и Р_А=44,7788 мбар; выше на 40 км Т=250,35 К и Р_А=2,87143 мбар; на 8,3 км - Т=234,27 К и Р_А=341,355 мбар; составит в видимом сегменте оптических волн соответственно 5,72×10^-4км^-1; 3,193×10^-5 км^-1 и 4,057×10^-3 км^-1; в ближнем инфракрасном участке спектра 8,0743×10^-5 км^-1 и 4,505×10^-6 км^-1 и 5,725×10^-4 км^-1 соответственно; а также в средневолновом инфракрасном диапазоне - 2,36×10^-7 км^-1 и 1,3×10^-8 км^-1 и 1,673×10^-6 км^-1. Это означает, что оптические толщи прослоек околоземной газовой среды /„ геометрической толщиной (636,8723 км и 408,1277 км) равны

; соответственно 1,302 и 0,9448 в отрезке 0,38… 0,76 мкм оптических волн; соответственно 0,18375 и 0,1333 в интервале 0,76…1,1 мкм спектра; соответственно 5,37×10^-4и 3,9×10^-4 в участке 3,0…5,0 мкм. Способ сложения слоев теории переноса радиации физической оптики предоставляет право определить оптическую толщину всего атмосферного слоя на трассе от объекта разведки до средства наблюдения и коэффициент пропускания такого отрезка околоземной газовой среды

. В результате оптическая толща и коэффициент пропускания слоя атмосферы на наклонном пути размером 1045 км в видимой, ближней инфракрасной и средневолновой инфракрасной областях спектра соответственно 2,2467 и 0,10575; около 0,317 и 0,7283; порядка 9,27×10^-4 и 0,99907.where σ _mol . (h, λ _EMI ) is an indicator of molecular scattering of electromagnetic with a wavelength λ _EMI oscillations at h height above sea level;

= 1013 mbar; P _{A is the} atmospheric pressure at a height h above the landscape of the Earth; T ₀ = 273.15 K; T is the atmospheric temperature at a height h above the earth's surface; λ [μm] is the wavelength of radiation; GOST 4401-81 “The atmosphere is standard. Parameters ”leads: at an altitude of 21.35 km, T = 217.929 K and Р _А = 44.7788 mbar; 40 km higher than T = 250.35 K and P _A = 2.87143 mbar; at 8.3 km - T = 234.27 K and Р _А = 341.355 mbar; will be in the visible segment of optical waves, respectively, 5.72 × 10 ^-4 km ^-1 ; 3.193 × 10 ^-5 km ^-1 and 4.057 × 10 ^-3 km ^-1 ; in the near infrared part of the spectrum, 8.0743 × 10 ^-5 km ^-1 and 4.505 × 10 ^-6 km ^-1 and 5.725 × 10 ^-4 km ^-1, respectively; as well as in the mid-infrared range - 2.36 × 10 ^-7 km ^-1 and 1.3 × 10 ^-8 km ^-1 and 1.673 × 10 ^-6 km ^-1 . This means that the optical strata of the interlayers of the near-earth gaseous medium / „with a geometrical thickness (636.8723 km and 408.1277 km) are equal

; respectively 1,302 and 0,9448 in the segment of 0.38 ... 0.76 micron optical waves; respectively 0,18375 and 0.1333 in the range of 0.76 ... 1.1 μm of the spectrum; respectively 5.37 × 10 ^-4 and 3.9 × 10 ^-4 in the area 3.0 ... 5.0 μm. The method of adding layers of the theory of radiation transfer of physical optics provides the right to determine the optical thickness of the entire atmospheric layer on the route from the object of intelligence to the means of observation and the transmittance of such a segment of near-earth gas environment

. As a result, the optical thickness and transmittance of the atmospheric layer on an inclined path measuring 1045 km in the visible, near infrared and medium-wave infrared spectral regions are 2.2467 and 0.10575, respectively; about 0.317 and 0.7283; about 9.27 × 10 ^-4 and 0.99907.

- коэффициент пропускания и F_ос - апертура - диафрагменное число - оптической системы. К примеру, τ_ос равно 0,95 у опытного сверхсветосильного объектива с мультипросветлением «Волна-8 50/1,2» дальномерных телекамер; у оптической сверхсветосильной системы с мультипросветлением «Зенитар 0,95/50 Е» F_oс составляет 0,95. Эти цифры констатируют об интегральной облученности матрицы фотодетектора 5,097×10^-6 Вт/м² в области 0,38…0,76 мкм оптических волн, если численная величина 0,263 характеристики объектива τ_ос/(4×F_oс ²). В полосе спектра 0,76 …1,1 мкм не реализуется мультипросветление оптических систем, поэтому в расчетах применяют стандартное значение τ_oс=0,85 объектива. Интегральная освещенность массива фотодетектора фотоприемника телекамеры в ближнем инфракрасном сегменте оптического спектра 3,141×10^-5 Вт/м² в этом случае. Величины энергетических облученностей 5,097×10^-6 Вт/м² и 3,141×10^-5 Вт/м² на двумерных матрицах ELCM 1075 и ELCM 1077 фотоприемников S3C/075 и S3C/077 телекамер с объективами «Зенитар 0,95/50 Е» (ПАО «Красногорский завод им. С.А. Зверева») означают, что в пикселах массивов за период времени экспонирования t_H будет накоплен пакет зарядов в N_e электронов [Уваров Н.Е. Секреты высокой чувствительности ТВ камер // Алгоритм безопасности. 2002.Then the plasma formation luminosity with an intensity of 2 × 10 ⁸ W will create an integral irradiance of 1.9368 × 10 ^-5 W / m ² in the visible and 1,334 × 10 ^-4 W / m ² in the near-infrared segments of optical waves on lens cut-offs, taking into account the law Allard (squares of distances). The illumination of the photodetector photodetector array of television cameras significantly depends on the characteristics of their lenses

- transmittance and F _oc - aperture - f-number - of the optical system. For example, τ _os is equal to 0.95 for an experienced super-powerful lens with a multi-luminosity "Wave-8 50 / 1.2" rangefinder camera; for the optical Zenitar 0.95 / 50 E optical super- _lumen system, F _oc is 0.95. These figures state the integral irradiance of the photodetector's matrix of 5.097 × 10 ^-6 W / m ² in the region of 0.38 ... 0.76 μm optical waves, if the numerical value of 0.263 is the objective characteristic τ _oc / (4 × F _oс ² ). In the spectral band 0.76 ... 1.1 μm, the multi-clarification of optical systems is not realized, therefore, the standard value τ _oc = 0.85 of the lens is used in the calculations. The integrated illumination of the photodetector photodetector array of the camera in the near-infrared segment of the optical spectrum is 3.141 × 10 ^-5 W / m ² in this case. The magnitudes of energy irradiations of 5,097 × 10 ^-6 W / m ² and 3.141 × 10 ^-5 W / m ² on two-dimensional matrices of ELCM 1075 and ELCM 1077 S3C / 075 and S3C / 077 cameras with Zenitar 0.9 / 50 E lenses (PJSC "Krasnogorsk Plant named after S.A. Zverev") means that in pixels of arrays during the exposure time period t _{H a} package of charges will be accumulated in N _e electrons [Uvarov N.Е. Secrets of high sensitivity of TV cameras // Security Algorithm. 2002

;

;

[Bт/м²] - облученность на кристалле массива; а²[м²] - площадь пиксела матрицы; η(λ_ЭМИ) - квантовая эффективность массива; W_ф(λ_ЭМИ) [Дж] - энергия фотона;

; с - скорость света в вакууме (с=2,9979×10⁸ м/с);

-константа Планка (

=6,6262×10^-34 Дж/Гц); W_Ф(0,57 мкм)=3,485×10^-19 Дж; W_Ф(0,93 мкм)=2,257×10^-19 Дж; t_H=0,125 с (с целью временной синхронизации функционирования телекамер и тепловизора, так как в нем циклы накоплений фотонов полей кадров длятся 0,125 секунд).Where

[W / m ² ] - irradiance on the crystal array; and ² [m ² ] is the pixel area of the matrix; η (λ _EMI ) is the quantum efficiency of the array; W _f (λ _EMR ) [J] is the photon energy;

; c is the speed of light in vacuum (c = 2,9979 × 10 ⁸ m / s);

-constant Planck (

= 6.6262 × 10 ^-34 J / Hz); W _F (0.57 microns) = 3,485 × 10 ^-19 J; W _F (0.93 μm) = 2.257 × 10 ^-19 J; t _H = 0.125 s (for the purpose of time synchronization of the cameras and the thermal imager, as it contains cycles of photon accumulation of field fields of 0.125 seconds).

и

. В этих зарядовых пакетах количество

- электроны фотонного шума, к которым добавляется число электронов шума считывания величиной, как правило, не более 10…20 электронов [Неизвестный С.И., Никулин О.Ю. Приборы с зарядовой связью - основа современной телевизионной техники. Основные характеристики ПЗС//Специальная техника. 1999. №5. С. 30-38]. В таком случае превышения амплитуд полезных сигналов над уровнем шума на выходах фотоприемников достигнут 7,4 и 24 раза соответственно. Процедура алгоритмического сложения цифровых кадров фотоприемников типа S3C/077 и S3 С/075 способствует реализации суммарного значения отношения размаха полезного колебания к шумовой дорожке ψ_Σ [Тарасов В.В., Якушенков Ю.Г. Инфракрасные системы "смотрящего" типа. М.: Логос, 2004]:

Provided the photo detectors are activated: S3C / 077 in the visible and S3C / 075 in the near infrared range of the optical spectrum, - the elements of the matrices of their photodetectors in their potential wells will accumulate 267 electrons

and

. In these charge packets, the number

- electrons of photon noise, to which the number of electrons of a readout noise is added, usually not more than 10 ... 20 electrons [Unknown S.I., Nikulin O.Yu. Charge-coupled devices are the basis of modern television technology. The main characteristics of the CCD // Special equipment. 1999. №5. Pp. 30-38]. In this case, the amplitudes of the useful signals exceed the noise level at the photodetector outputs and reach 7.4 and 24 times, respectively. The procedure of algorithmic addition of digital frames of photodetectors such as S3C / 077 and S3 С / 075 contributes to the realization of the total value of the ratio of the range of useful oscillations to the noise track ψ _Σ [Tarasov VV, Yakushenkov Yu.G. Infrared systems "looking" type. M .: Logos, 2004]:

- величина превышения амплитуды полезного сигнала над уровнем шума на выходе фотоприемника соответственно видимого отрезка и ближнего инфракрасного участка оптического спектра; около 25 раз. Согласно графическим представлениям ("кривым обнаружения" излучений с неизвестной амплитудой и фазой статистики Неймана-Пирсона) достоверности регистрации цели, равенство в 25 раз величины ψ_Σ равнозначно близкой к единице вероятности правильного обнаружения. Основан выбор в качестве объекта разведки совокупности теплоизлучающих образования плазмы и раскаленного вихревого потока на следующем. В ходе определения расстояния до источника инфракрасных излучений оптического спектра используются закономерности теории критериев Джонсона, которые позволяют с определенной степенью достоверности утверждать об успешном решении оператором задач наблюдения панорам (восприятия его зрительным анализатором и интерпретации изображения). Правильное обнаружение цели оператором, согласно модели функционирования "смотрящего" тепловизора, адекватно разрешению им соответствующей штриховой миры тест-объекта с показателями: радиационный контраст, пространственная частота, размеры и количество штрихов миры, - определяющими рубежи ее выделения и степень сложности задач разведки. Размер тест-объекта принимают в виде квадрата с равной поверхности визируемой цели площадью и HT-O сторонами. Число NP - заполняющих квадрат штрихов миры устанавливает вероятность правильного обнаружения теплоизлучающего объекта. Дальность выделения цели находят из равенства ее радиационного контраста с имеющимся фоном, приведенного расчетом к входному зрачку фотоприемника тепловизора, - чувствительности его фото детектора - минимальной разрешаемой разности температур (МРРТ) [Тарасов В.В., Якушенков Ю.Г. Инфракрасные системы "смотрящего" типа. М.: Логос, 2004]: ; где ΔTЦ-Ф - тепловая контрастность объекта на окружающем фоне. Диапазон температур цели 1000…2500°К при температуре слоев атмосферы 250,35° К на высоте 40 км над уровнем моря, а также равенство 0,99907 коэффициента τатм.(3,0…5,0 мкм) свидетельствуют о необходимости применения тепловизора с МРРТ≤748,953°К показателем. Даже в самых благоприятных условиях дальность обнаружения тепловизором объекта разведки

ограничивают его размер и технические показатели (фокусное расстояние объектива, формат и площадь пикселов фотодетектора) инфракрасной камеры [Никитин В.В., Цыцулин А.К. Телевидение в системах физической защиты. СПб.: СП6ТЭТУ "ЛЭТИ", 2001]:Where

- the magnitude of the excess amplitude of the useful signal above the noise level at the output of the photodetector, respectively, the visible segment and the near-infrared portion of the optical spectrum; about 25 times. According to the graphical representations (“detection curves” of radiation with an unknown amplitude and the phase of the Neumann-Pearson statistics) of the accuracy of target registration, the equality of раз _{Σ by} 25 times is equivalent to a unit probability of correct detection. Based on the choice of the object of exploration of a set of heat-emitting plasma formation and red-hot eddy flow on the following. In determining the distance to the source of infrared radiation of the optical spectrum, laws of the Johnson criterion theory are used, which make it possible to assert with a certain degree of certainty that the operator has successfully solved the panorama observation tasks (perceiving it with a visual analyzer and interpreting an image). Correct detection of the target by the operator, according to the operating model of the “looking” thermal imager, is adequate to resolving the corresponding test object world with the following parameters: radiation contrast, spatial frequency, size and number of world strokes - defining the frontiers of its separation and degree of difficulty of reconnaissance tasks. The size of the test object is taken in the form of a square with an equal surface of the target to be targeted and its area and HT-O sides. The number of NPs - the square-filling strokes of the worlds sets the probability of correctly detecting a heat-emitting object. The target extraction range is found from the equality of its radiation contrast with the available background, reduced by calculation to the entrance pupil of the thermal imager of the photodetector, - the sensitivity of its photo detector - the minimum allowable temperature difference (MRRT) [Tarasov VV, Yakushenkov Yu.G. Infrared systems "looking" type. M .: Logos, 2004]:; where ΔTЦ-F is the thermal contrast of the object on the surrounding background. The temperature range of the target is 1000 ... 2500 ° K at an atmospheric layer temperature of 250.35 ° K at an altitude of 40 km above sea level, and the equality of the 0.99907 ratio parameter (3.0 ... 5.0 μm) indicates the need to use a thermal imager with MPPT≤748,953 ° K indicator. Even in the most favorable conditions, the detection range of a reconnaissance object by a thermal imager

limit its size and technical indicators (focal length of the lens, format and area of pixels of the photodetector) of an infrared camera [Nikitin VV, Tsitsulin AK Television in physical protection systems. SPb .: SP6TETU "LETI", 2001]:

;

;

- фокусное расстояние объектива; h_M- высота матрицы фотодетектора; Δ_отн.- размер цели в пересчете на высоту растра массива; для ее обнаружения в поле зрения тепловизора теория критериев Джонсона предписывает в кадре иметь в пределах проекции его высоты не менее двух строк разложения, либо Δ_отн.[%]⁼(2/N_строк)×100%; здесь N_строк - число строк матрицы фотодетектора. Это означает, что обнаружение тепловизором с 50 мм фокусным расстоянием объектива и фотоприемником с фотодетектором МФПУ-С формата 512×640 пикселов площадью 25×25 мкм визируемого объекта возможно при равенстве не менее 1045 м его h_Т-О геометрического размера. Такую протяженность могут иметь только плазменное образование и раскаленный вихревой поток "следа в атмосфере" гиперзвуковой цели. Аппроксимацию показателей тепловизора в моделях ослабления термальной радиации объекта атмосферой представляют следующими соотношениями [Трестман М.М. Обнаружение крылатой ракеты прибором ночного видения / Материалы Научной конференции "Актуальные проблемы в прикладных научных исследованиях". Арад, Реховот (Израиль): ИПИ, декабрь 2012. С.233-239]:

; где

с в экспоненциальной аппроксимации МРРТ; РТЭШ=25 мК характеристика эквивалентная шуму разность температур прибора МФПУ-С; здесь δ_эл - элементарное поле зрения тепловизора; при

=50 мм и 25 мкм - длине грани пиксела - δ_эл=0,5 мрад.; ω_м- пространственная частота миры;

; откуда следует:

;где

- это требуемая дальность обнаружения физического тела h_т-о размером; достигнет 1,826 значения. В теории критериев Джонсона численные величины N_P=3;2 и 1,75 означают вероятности правильного обнаружения соответственно 1,0; 0,95 и 0,9 [Тарасов В.В., Якушенков Ю.Г. Инфракрасные системы "смотрящего" типа. М.: Логос, 2004], следовательно N_P=1,826 равнозначно вероятности 0,93 (и более) правильного обнаружения совокупности плазменного образования с раскаленным вихревым потоком "следа в атмосфере" гиперзвукового объекта. Выбор отражающего радиацию Солнца конденсационного шлейфа в качестве объекта разведки основан на следующем. Формирующийся за движущимся на гиперзвуке в плотном воздухе летательным аппаратом конденсационный или "паровой"шлейф (англ. "vapour trail) это облачный, из сконденсировавшихся на метеоритной пыли (ее попадает в приземную газовую среду около 100 тыс.тонн ежегодно) мелких частиц (типового размера от 50 до 200 нм) в основном атмосферной влаги и в меньшей степени водяных паров выхлопов, выбросов из двигателя, след - результат их мгновенной кристаллизации и сублимации -искусственное, из микрокристаллов льда и микроскопических капелек влаги, перисто-кучевое облако верхнего яруса класса "Cirrocumulus tracft - "Сi trac", "Cirrus tract'' (с новолатин. "дорожное"), ледяные микрокристаллы в котором по структуре подобны снежинкам свежевыпавшего снега. Числовые величины альбедо свежевыпавшего снега в зависимости от длин волн света, падающего на него [Рек. МСЭ-R RS.1804 Рекомендация МСЭ-R RS.1804* "Технические и эксплуатационные характеристики систем спутниковой службы исследования Земли, работающих на частотах выше 3000 ГГц" (Вопрос МСЭ-R 235/7), 2007], равны 0,98 и 0,87 в видимом и ближнем инфракрасном участках оптического спектра соответственно. Тогда с достаточной для расчетов точностью альбедо поверхности конденсационного шлейфа можно учитывать 0,95 и 0,85 в полосе 0,38…0,76 мкм и в сегменте 0,76…1,1 мкм соответственно. Облученность на массиве фотоприемника телекамеры зависит от освещенности на объекте, ряд типовых значений которой приводится в [Неизвестный С.И., Никулин О.Ю. Приборы с зарядовой связью - основа современной телевизионной техники. Основные характеристики ПЗС//Специальная техника. 1999. №5. С. 30-38], к примеру, при средней прозрачности атмосферы находящаяся в зените полная Луна освещает плоскость по нормали к ее лучам с 0,25 лк интенсивностью; во время безлунной ночи 0,02 лк степень облучения площадки. Интенсивность в 1 Вт=1 Дж/с солнечного излучения в спектре кривой видимости зрительного анализатора соответствует световому потоку в 220 лм; то есть энергетическая облученность 1 Вт/м²=220 лк световой освещенности в видимом диапазоне и интегральная облученность 1 Вт/м²≡181 лк световой освещенности в 0,76… 1,1 мкм области оптических волн. Это означает, что ночью при полной Луне и в ночной безлунный период суток энергетическая облученность на плоскости составляет 1,1363×10^-3 Вт/м² и 9,09×10^-5 Вт/м²в диапазоне 0,38…0,76 мкм оптического спектра соответственно и 1,3812×10^-3 Вт/м² и 1,104×10^-4 Вт/м² в ближнем инфракрасном участке оптических излучений соответственно. Тогда интегральная освещенность на матрице фотодетектора фотоприемника:Where

- focal length of the lens; h _M - height of the photodetector matrix; Δ _rel. - target size in terms of the height of the array raster; To detect it in the field of view of a thermal imager, Johnson's criterion theory prescribes that within a frame, within the projection of its height, at least two decomposition lines, or Δ _rel . [%] ⁼ (2 / N _lines ) × 100%; here N _rows is the number of rows of the photo detector matrix. This means that the detection of the thermal imager with a 50 mm focal length lens and photodetector with a photodetector MFP-C format 512 × 640 pixel area of 25 × 25 microns viziruemogo object may with equal at least 1045 h _T his _m-O geometric size. Such a length can have only the plasma formation and the heated vortex flow "trace in the atmosphere" hypersonic target. The approximation of the thermal imager indices in models of attenuation of thermal radiation of an object by the atmosphere is represented by the following relations [Trestman M.M. Detection of a cruise missile with a night vision device / Materials of the Scientific Conference "Actual problems in applied scientific research." Arad, Rehovot (Israel): IPI, December 2012. P.233-239]:

; Where

with exponential approximation of MRRT; RTES = 25 mK characteristic noise equivalent temperature difference of the device MFPU-S; here δ _el - the elementary field of view of the imager; at

= 50 mm and 25 μm - the length of the pixel face - δ _el = 0.5 mrad .; ω _m - spatial frequency of the worlds;

; where it follows from:

;Where

- This is the required range of detection of the physical body h _t-o size; will reach 1,826 values. In the Johnson criterion theory, the numerical values N _P = 3; 2 and 1.75 mean the probabilities of correct detection, respectively, 1.0; 0.95 and 0.9 [Tarasov VV, Yakushenkov Yu.G. Infrared systems "looking" type. M .: Logos, 2004], therefore N _P = 1,826 is equivalent to the probability of 0.93 (or more) of the correct detection of a set of plasma formation with a heated vortex flow "trace in the atmosphere" of a hypersonic object. The choice of a condensation plume reflecting the radiation of the Sun as an object of exploration is based on the following. The condensation or “steam” plume (eng. ”Vapour trail) formed behind an airship moving in dense air is cloudy, from small particles (of a typical size) that condense on meteorite dust (it enters the surface gas environment about 100 thousand tons). from 50 to 200 nm) mainly atmospheric moisture and, to a lesser extent, exhaust water vapor, emissions from the engine, the trace is the result of their instant crystallization and sublimation — artificial, from ice microcrystals and microscopic droplets of moisture, pinnacular The first cloud of the upper tier of the class "Cirrocumulus tracft -" Сi trac "," Cirrus tract '' (from Novolatin. "Road"), ice microcrystals in which are similar in structure to snowflakes of freshly falling snow. Numerical values of the albedo of freshly falling snow depending on the wavelengths of light falling on it [Rec. ITU-R RS.1804 Recommendation ITU-R RS.1804 * “Technical and operational characteristics of Earth exploration-satellite service systems operating at frequencies above 3,000 GHz” (Question ITU-R 235/7), 2007 ], equal to 0.98 and 0.87 in the visible and near-infrared parts of the optical spectrum, respectively stately. Then, with the albedo surface of the condensation plume sufficient for the calculations, it is possible to take into account 0.95 and 0.85 in the 0.38 ... 0.76 μm band and in the 0.76 ... 1.1 μm segment, respectively. Irradiation on the camera array of a photodetector depends on the illumination on the object, a number of typical values of which is given in [Unknown SI, Nikulin O.Yu. Charge-coupled devices are the basis of modern television technology. The main characteristics of the CCD // Special equipment. 1999. №5. Pp. 30-38], for example, with an average transparency of the atmosphere, the full Moon at the zenith illuminates the plane normal to its rays with 0.25 lux intensity; during a moonless night 0.02 lux the degree of exposure to the site. The intensity of 1 W = 1 J / s of solar radiation in the spectrum of the visibility curve of the visual analyzer corresponds to a luminous flux of 220 lm; that is, the energy irradiance of 1 W / m ² = 220 lx of the light illumination in the visible range and the integral irradiance of 1 W / m ² ≡ 181 lx of the light illumination in the 0.76 ... 1.1 μm region of optical waves. This means that at night with a full moon and during a nightless moonless day, the energy irradiance on the plane is 1.1363 × 10 ^-3 W / m ² and 9.09 × 10 ^-5 W / m ² in the range of 0.38 ... 0, 76 μm of the optical spectrum, respectively, and 1.3812 × 10 ^-3 W / m ² and 1.104 × 10 ^-4 W / m ² in the near-infrared part of the optical radiation, respectively. Then the integrated illumination on the photodetector photodetector matrix:

в области оптических излучений 0,38…0,76 мкм, и

в интервале электромагнитных волн 0,76…1,1 мкм соответственно ночью при Луне в зените и в безлунный ночной период суток. Эти пакеты зарядов сформируют на выходах цифровых фотоприемников радиации 6,38…0,76 мкм и 0,76…1,1 мкм оптических волн превышение амплитуды полезного сигнала над уровнем шума в 26 и 76,85 раз в ночной период суток при нахождении в зените полной Луны, а также четыре и 14,3 раза во время темной безлунной ночи. Последнее вызывает потребность применения алгоритмического сложения цифровых снимков фотоприемников S3C/077 и S3C/075, которое создаст суммарную величину отношения размаха полезного колебания к шумовой дорожке 14,85 раз. Численное значение 14,85-кратного превышения амплитуды полезного сигнала над размахом шумов на выходе сумматора реализует вероятность правильного обнаружения 0,95 при 10^-4 темпе ложных тревог. В этом случае геометрический размер визируемого объекта должен быть не менее 669 метров.here E _e - energy irradiance at the facility; lens characteristic {τ _OS / (4 × F _OS ² )} = 0.263 (super-fast with multi-enhancement) in the 0.38 ... 0.76 μm wavelength range; {τ _OS / (4 × F _OS ² )} = 0,235457 (super-strong) in the near-infrared segment of optical waves; will be equal at night in the full moon and in the nightless moon period 3 × 10 ^-5 W / m ² and 2.4 × 10 ^-6 W / m ^2, respectively, in the visible band of the optical spectrum, as well as 2 × 10 ^-4 W / m ² and 1.516 × 10 ^-5 W / m ^2, respectively, in the 0.76 ... 1.1 μm portion of the wavelengths. With an equality of 0.125 s exposure cycle and the use of S3C / 077 photodetector in the visible and S3C / 075 - in the near-infrared ranges of the optical spectrum - in their photodetectors the matrix pixels will accumulate in their potential wells charge packets

in the field of optical radiation 0.38 ... 0.76 microns, and

in the range of electromagnetic waves of 0.76 ... 1.1 μm, respectively, at night with the Moon at the zenith and during the moonless night period of the day. These packets of charges will form at the outputs of digital photodetectors of radiation 6.38 ... 0.76 microns and 0.76 ... 1.1 microns of optical waves, the excess of the amplitude of the useful signal above the noise level 26 and 76.85 times during the night period of the day when at the zenith the full moon, as well as four and 14.3 times during a dark moonless night. The latter raises the need for the application of algorithmic addition of digital images of photodetectors S3C / 077 and S3C / 075, which will create a total value of the ratio of the range of useful oscillations to the noise track 14.85 times. The numerical value of the 14.85-fold excess of the amplitude of the useful signal over the range of noise at the output of the adder realizes the probability of correct detection of 0.95 with a 10 ^-4 rate of false alarms. In this case, the geometric size of the object to be sighted must be at least 669 meters.

The choice of a decisive geometric and dynamic object, as well as trajectory unmasking signs of its "trace in the atmosphere" as a criterion, involves combining the image of heat-emitting plasma formation and red-hot vortex flow with images of light-emitting plasma formation, light-reflecting condensation plume into a single image (see Fig. 2 ). In ensuring the coordinated operation of the thermal imager and cameras, which generate their own series of sync signals, one of the main problems is the synchronization of their functioning. Due to the fact that the mid-wave infrared spectral channel of an optical radiometer provides priority signs of a "trace in the atmosphere" of the object of reconnaissance (the flight of a physical body on a hypersound in the near-earth gas environment means the formation of plasma layers and a hot vortex flow around it; 3.0 ... 5, 0 μm interval of wavelengths is less than the attenuation of optical radiation), then the scheme of rigid synchronization of the system of passive observation by the sync signals of the medium-wave infrared thermal imager is used (see Fig. 2). In this scheme, for (so-called "slave") cameras of the visible and near-infrared ranges of optical waves, a synchronization frame of shooting with a half-pixel version of "digital reference" is used. As a result, the system central computer will form an “optical portrait” of the target, which, subject to the availability of an “almanac” of images of typical objects, will contribute to solving the problem of recognizing an aircraft. Further, in order to find the dynamic, trajectory distinctive criteria, the measured angles of the anterior cut of the formation of a "trace in the atmosphere" plasma in the form of target designation are issued by the central computer to the active, on the principles of radio photonics, radar of the meter range of radio waves. With a radio wavelength of 4 ... 6 m for the formation of radiation patterns with a divergence of 0.1 ang. hail, antenna devices are required that are 100 times the wavelength of radio signals. It is possible to place such an antenna on a significant volume of a shell of a motorized airship or an unmanned aeronautical device. On the principles of radiophotonics, low-frequency radars for unmanned aeronautic vehicles, which are planned to be adopted by the VKS of Russia in 2020–25, are created by the Concern Radioelectronic Technologies, JSC. The new technology combines radiators and receivers of radioelectronic devices with optical elements, in which radio-photon analog-digital converters form optical signals from radio oscillations and vice versa, which allows the use of fiber-optic communication lines - to reduce weight and self-noise, instead of coaxial cables and waveguides. dozens of times to improve the resolution and galvanically unleash metal cascades of amplifiers and antennas, to carry out fully digital processing of radio waves. A radar with a wavelength of radio emission of 4 ... 6 m is used only to measure the distance to an object detected by an optical radiometer in order to determine its motion parameters, the first of which is the ground speed. Since in the field of view of the thermal imager and television cameras torches of emissions from power plants operating in the afterburner mode (with a temperature of more than 2000 ° K), red-hot vortex flows, condensation plugs of supersonic combat aircraft may fall, in particular cases false registration schemes may occur. Therefore, in the process of detecting an object flying at a hypersound by its “trace in the atmosphere” with an optical radiometer, the selection of a target according to a dynamic decisive criterion is a mandatory procedure. Following it, the motion parameters are tracked along a trajectory basis — to exclude meteorite (bolide) targets from further analysis. Comprehensive use in the technical solution as an extensive “trace in the atmosphere” contrasting with the background of the object of study, as spectral channels of an onboard optical radiometer of an unmanned aeronautical device — equipped with thermal and light radiation photodetectors MFPU, S3C / 075 and S3C / 077 photo-detectors based on two-dimensional arrays - a precision thermal imager and television cameras placed in space, taking into account the passage of the line of sight over the five-kilometer-long "lower" layer of the troposphere Denia purpose - provides opportunity to implement its registration in the range 1045 km with correct detection probability P _ON = 1- (1-0,999) × (1-0,93 ) × (1-0,95) = 0,999997 during dark moonless nights.

Building unmanned aeronautical vehicles into battle order with a distance of 150 ... 200 km between them, using thermal imagers and television cameras from 45 angles. hail, sectors of the review (with a focal length of optical systems of 50 mm) with photodetectors MFPU-S, S3C / 077 and S3C / 075 (the elementary field of view is 1.72 angular minutes; 1.1 angular minutes and 0.923 angles. min.) per 1045 km, the specified search range will form a reconnaissance field having the following characteristics: a zone of controlled airspace of 820.74 × 820.74 km with the possibility of measuring the angles of the object to be viewed with a maximum error, respectively: 0.86 ang. min and 0.55 ang. min and 0.462 ang. min - digital processing by the video processor of the matrix photodetector signals realizes the determination of the coordinates of the radiator with an accuracy of tenths and hundredths of an element (pixel) of the photosensitive array. The detection of the motion path - avtozakhv on escort - the object, the construction of the route of its flight - observation - and calculating from 0.125 with the data update cycle, in the interests of the consumer, the traveling central parameters of the location of the target in space are performed by the system’s central computer of the optical radiometer (after receiving information about object of intelligence - from the active radar) in the process of functioning of its algorithms for the primary analysis of images and the secondary processing of optical information (images). Studies conducted in the United States showed that, as applied to images of typical weapons and military equipment in the range of 0.95 ... 1.0, there is a probability of their detection, recognition and identification if the number of pixels placed along a critical target target — the Johnson number — is equal to 2 ... 3; from 6 ... 9 to 8 ... 12 and 12 ... 18 [Tarasov VV, Yakushenkov Yu.G. Infrared systems "looking" type. M .: Logos, 2004]. In the tracking-aiming mode, compared with the search-detect stage, the focal length of the thermal imager lens and the television camera should be increased by no less than four times, that is, up to 200 mm or more.

The system of long-range radio-electronic reconnaissance of a “radio-invisible” flying at a hypersonic speed in the stratosphere, an object, according to the signs of its “trace in the atmosphere”, serves as a destination as follows. The review sector assigns to each on-board optical radiometer of "floating" in the height range of the "windpause" unmanned aeronautic apparatuses, based on data on the technical condition of their payload and external meteorological situation, a digital computer complex of the ground reference point for information processing and control. In a responsible or given sector, 45 × 45 coal. hail, spectroscopic spectral channels of an optical radiometer passively detect targets (the total area of the airspace controlled by the search and tracking complex at a distance of 1045 km can reach 820.7 × 2450 km); when registering a "trace in the atmosphere" of a probable object of intelligence, they capture the front sections of plasma formation and the condensation plume of the object of exploration for tracking. The system central computer of an onboard optical radiometer of an unmanned aeronautic apparatus transmits commands to spectral channels to switch to tracking-aiming mode, that is, switching 50 mm short-focus lenses to long-focus 200 mm optical systems of a thermal imager and television cameras. They narrow in this case, the review sector to 8.5 coal. hail, with reduction to 27.78 coal; 16.5 coal pulses and 14.44 coal pulses of elementary visual fields — when using the MFPU-S, S3C / 077, and S3C / 075 photodetectors, respectively. In the form of target designation, these coordinates of the angles of the front sections of the plasma formation and the condensation loop are given to the active radar meter radio waves on the principles of radio photonics to determine the removal of the ion-electronic simulator. After calculating the motion parameters of the target, the images in the visible and near infrared, mid-wave infrared bands of the optical spectrum of the current observation panoramas, the coordinates of the location and the image of the "portrait", the track indicators of the location change are transmitted via the radio data exchange link to the ground information processing and control center. This information is automatically transmitted to the reference POI and U (for the purpose of subsequent assessment of image quality, selection of the priority observation and sighting post, recognition of the image of the object of reconnaissance), as well as spatial coordinates, movement parameters are given to the command center of the anti-aircraft missile system (CP ZRS) for preparation of firing data. The elementary fields of view of the cameras 14.44 ang. S and 16.5 ang. S and the thermal imager 27.78 ang. S realize the positioning of the plasma formation front with 73.2 m and 83.6 m and 130.625 m geometrical accuracy. Combined with measurement errors of the range to the target being shot (~ 400 m) by radar meter radio waves, errors in ~ 100 m of the angle coordinate measurement are acceptable on the marching trajectory interval when controlling the anti-missile with an active radar homing head, since by the time it approaches the attacked object the on-board radiator switching-on distance to supersonic, about 1200 m / s - the hypersonic speed of such a target will decrease (see p. 9), and the plasma envelope will disappear making it “radio-invisible”. In an optical radiometer, the channels for detecting a light-emitting “cocoon” of plasma-1, recording a reflective KSH-2 consist of: 4 optical systems, transducer blocks (photoelectric and analog-digital) - 5, buffer memories (bit image storage) - 6, video processors (the continuum of the pixel-by-pixel signal processing module - 7 and 8 - the image contour extraction module - in Fig. 2). The image of the sighted panorama of space is projected by lenses 4 onto the photosensitive planes of photoelectric transducer crystals (or matrix photodetectors), which convert the light waves incident on them into electrical oscillations and transmit the latter to analog-to-digital converters. From their outputs, digital signals, in the form of parallel binary codes, arrive in buffer memories 6 of the storage of bit images of the area of interest, - their capacity determines the format of the photo detector matrix. Each digital image recorded in the buffer memory, is "viewed" in the module pixel-by-pixel processing of signals 7 video processor photodetector. Registration of “point” reconnaissance objects does not require the allocation of their contours or shapes, therefore, in the detection channel of the light-emitting plasma “cocoon” 1 of 7 — the pixel-by-pixel processing module, digital data in parallel arrive at 8 — the video contour image extraction module — to perform the addition of signals from neighboring cells array (based on the distribution of irradiance in the image of a “point” target, a rotational Gaussian), and if this image occupies several elements, then the optical energy per such pixel is found the solution of the system of equations for the number of irradiated cells of the matrix by the method of "least squares") - the "binning" of frames and the system central computer 11 of the optical radiometer. A digital code from the image contour extraction module 8 is output to 10 — an image mixing device and from it — to the system central computer 11 of an optical radiometer. The observation channel of heat-emitting plasma clouds and RAH - 3 consists of 4 - optical systems, a block of transducers (photoelectric, analog-digital) 5, a buffer memory device - 6 - storage of a bit image, a video processor (assembly of modules 7 - pixel-by-pixel signal processing and 9 - corrections Images). From the structure of the channels for detecting a light-emitting plasma “cocoon” 1 and registering a reflective KSH 2, its scheme differs in that a digital image of the scene from the output of the buffer memory 6 as a parallel bit code is simultaneously output to a video processor (pixel-by-pixel signal processing modules 7 and image correction 9, where the program finds the adjacent irradiated elements for the "hot" cell of the matrix and groups them into a group, if they are no more than one pixel apart, and in 11 - a system central computer — as the infrared imager of the middle band of infrared waves measures the priority parameters of the reconnaissance objects. The video processor, after performing the initial processing of image frames, transmits them, for more complex transformations, to the system central computer 11. From the output of the image correction module 9, digital data is transmitted to the image mixing device 10, from which digital integrated frames are fed to the system central computer 11 of an optical radiometer . Such a structure of an optical radiometer creates an algorithmic binding to a set of heat-emitting plasma clouds and RAH — a light-emitting plasma “cocoon” to which the image of a retroreflective CG “attaches” —the system central computer forms a two-dimensional digital image of the “trace in the atmosphere” that meets the dynamic, trajectory, geometric criteria hypersonic "radio-inconsequential" object flying in the stratosphere - in real time.

The proposed solution allows to obtain a number of the following technical results. The round-the-clock frontier for electronic intelligence is based on signs of a “trace in the atmosphere” of a “radio-invisible” aerodynamic aircraft moving in the stratosphere on a hypersound of more than 1,045 km with at least 0.999997 probability. The trace track of the extended object of reconnaissance contrasting with the background of the sky and determining the coordinates of the front of the trace in the atmosphere in the search-detect mode with an error of 0.923 angles. min in the sector 45 coal. hail, together with the accuracy of measuring the distance of 400 m with a radar, and at the stage “tracking - aiming” - with an error of 14.44 angles. with in sector of 8.5 coal. hail. According to the criterion "efficiency - cost", the assessment is made as follows: on the priority of using as a stratospheric basing, geostationary - while maintaining a constant geographical position - a sight-seeing radio electronic station

intelligence equipped with an active radar meter radio waves and an optical radiometer unmanned aeronautic apparatus of the "Berkut" type - indicates its ability for 15 ... 20 years to conduct continuous, alternating 120 days of combat duty, 15 days of routine maintenance, monitoring the sector of responsibility, with lower financial costs which for periodically controlling the area of a disposable spacecraft (with a lifetime of 5 ... 7 years) constitute a numerical value, including launch costs, 4 ... 5 times ; for an airplane and a helicopter, the value is respectively 8 ... 10 and 15 ... 20 times, since they have a higher specific fuel consumption of 3 ... 4 and 14 ... 15 times, respectively, and also a much shorter duration of patrols.

Thus, the proposed technical solution allows:

1) to organize a round-the-clock frontier in 1045 km of radio-electronic reconnaissance on the basis of "trace in the atmosphere" moving "hypersonic" aerodynamic aircraft with a hypersonic speed in the stratosphere with at least 0.999997 detection probability - in the group of promising Aerospace firing air-defense missile systems Forces;

2) implement, with the errors necessary for the practice, tracking of targets in space, calculating, in the interests of consumers, the parameters of the movement of reconnaissance objects with an equal exposure cycle of 0.125 s — the period of accumulation of a shooting frame — updating information;

3) to provide the specified indicators of the survivability of the long-range electronic reconnaissance system of “radio-invisible” objects flying in the stratosphere on a hypersound, according to the signs of their “traces in the atmosphere” using passive mode of round-the-clock optical detection and target extraction, and operational reliability due to possible use as "hot reserve" of individual components of the controls and the system itself: it consists of 3 ... 4 unmanned aeronautic vehicles and from 3 to 4 ground processing points information and management; in each of them a set of universal automated workplaces consisting of three to four units; two dual-band spectral channels (near-infrared with visible) -tv cameras in the optical radiometer of the stratospheric geostationary radio electronic intelligence station;

4) to organize high-quality routine maintenance and current repair of electronic reconnaissance equipment and their carriers, thanks to one of the advantageous properties of an unmanned aeronautic device: those that do not require take-off and landing strips to the geostationary drift point and land at the place of scheduled maintenance;

5) to implement the required values of performance indicators (combat, technical and economic) of the electronic intelligence system of the airborne space hypersonic “radio-visible” percussion means due to the increase in the reality of target registration by the optical observation complex — by raising the informativity of two-dimensional images using it as an object of detection ( highlighting the image of a contrasting "trace in the atmosphere" of an aerodynamic aircraft.

Claims (2)

1. A method of long-range radio-electronic reconnaissance of a “radio-invisible” object flying in the stratosphere at a hypersonic speed, according to the signs of its “trace in the atmosphere”, including the registration of photon streams by photo-receivers of a thermal imager and television cameras of the spectral channels of an optical radiometer and secondary radio signals by radar meter radiowaves, characterized by to achieve maximum exploration range, choose the length of its object, formed by a hypersound flight in a continuous near-earth gas environment of this object, d in the atmosphere "of contrasting against the background of the sky of plasma formation and red-hot vortex flow, together forming an ion-electron train, and a condensation plume; determining the thermal contrast with the thermal imager plasma formation — background and red-hot vortex flow — background (difference of their radiation temperatures), azimuth and elevation of plasma formation, “point” target, coordinates of the angles of red-hot vortex flow, combined with television cameras along the line of sight of the thermal imager - brightness contrast plasma formation - background and condensation loop - background (difference of their brightness luminosities and albedo, respectively), azimuth and elevation angle of a “point” target - plasma formation, - coordinates of angles of a condensate an ion plume, assessing the angular coordinates of the plasma formation, behind it a hot vortex flow and after it a condensation plume line the target shape on one line relative to each other, measuring the radar meter radio waves - according to the coordinates of the plasma formation angles - the distance to the ion-electron simulator from the plasma formation, the heated whirl of the object of intelligence, calculating on the basis of its value - the speed of movement of the front section of the condensation plume and plasma formation, the angle of inclination of the vector sk horoshes to the local horizontal, - recognize the target as a "trace in the atmosphere" of an object flying at a hypersonic speed; receive photon fluxes and its secondary radio signals transmitted and reflected by the target “trace in the atmosphere” at the stratospheric observation and sighting post, respectively, by visible cameras, near-infrared regions of optical waves and infrared infrared optical spectrum thermal imager, radar meter radio waves; A sight-and-aim post is lifted to use the highest transparency of the medium between the vehicle and the photon exploration object — to eliminate the phenomenon of aerosol dissipation of their energy by the gas components of the air — a motorized stratostat or an unmanned aeronautic device — the Bercut airship into the corridor of “wind-pause”, “cycling” "stratosphere, at the same time, due to the unchanged direction and the lowest wind speed at these altitudes and the operation of the engines, they implement the regime of geostationary" drift "of the dirigible ; The azimuth and elevation angle of the target “trace in the atmosphere” are recorded with high-precision detectors of matrix photo-receivers of a digital thermal imager, cameras of an optical radiometer, with issuing target designation to the radar thoterics measuring the removal of the target of reconnaissance of meter radio waves; the accuracy of its ranging and determining the angular coordinates of the target “in the atmosphere” with a thermal imager, television cameras — their short or long focus modes, resolution or topology of discrete crystals of arrays of detectors of their photodetectors — define errors in calculating the location of the target object; the speed of its flight is considered to be equal to the speed of movement in the stratosphere of a plasma formation; the height of the reconnaissance object is found as a function of the distance and angle of the place of the "trace in the atmosphere" target, and the radius of the Earth. 2. A system for implementing the method according to claim 1, comprising three (or more) separated by a fixed distance in the base area, connected by radio links of data exchange of the stratospheric observation-target posts and three (or more) ground information processing and control points (one of them reference), characterized in that cameras are placed in the visible and near infrared and infrared infrared thermal imagers of the optical spectrum (with digital photodetectors on large-format array detectors) for recording azimuth and angle m These goals, and distance measurements of it, are active, on the principles of radiophotonics, meter radars on the "drift" at the heights of the "wind-wind pause" of the atmosphere of geostationary airships, unmanned aeronautical vehicles (motorized stratostats), rise 21 km above sea level of radio electronic stations reconnaissance when observing a reconnaissance object flying at a height of 40 km above the Earth's surface realizes the passage between them of photon fluxes over the five-kilometer "lower" region of the troposphere, where the phenomenon of aerosol scattering Ia gas components offline energy photons air; based on data on the technical status of unmanned aerial devices payloads and meteorological conditions in the area of their base, they set, at the ground control point for information processing and control, the sector of review for each optical radiometer, during combat use of sight-sight posts, after receiving at the ground processing point information and management of current personnel of onboard reconnaissance facilities of geostationary airships, analysis and evaluation of images - based on the quality of their images, change with Ktorov viewing optical radiometers "drifting" (keeping a constant geographic location of ground station data processing and control) motorized stratosphere; in the case of identifying a target in the atmosphere of a hypersonic reconnaissance object, a thermal imager, optical radiometer telecamera cameras are transferred to a long-tracking-aiming mode, its central system computer generates and gives target indication to an active radar measuring the distance of meter radio waves based on the principles of radiophotonics of geo-stationary reflectors, and in the range of meter-long radio waves, based on the principles of radiophotonics of the geo-stationary reflectors. working with radiation only during the period of determining the distance to the target; the calculation of its spatial coordinates of the location and values of the flight parameters of the reconnaissance object is algorithmically carried out by the central computer of the optical radiometer and the digital computer complex of the corresponding ground information processing and control center.

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