RU2517800C1 - Method of coelosphere coverage from space craft for surveillance of celestial bodies and coelosphere coverage space system for surveillance of celestial bodies and detection of solar system bodies to this end - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: proposed method of coelosphere coverage from space craft for surveillance of celestial bodies and coelosphere coverage space system for surveillance of celestial bodies and detection of Solar system bodies to this end. Survey consists in scanning of coelosphere by surveillance hardware in complete great circles or in sections composed by parts of said great circles at craft body spinning at preset velocity. Angular velocities of scanning are constant but differ for different coelosphere sections to allow registration of all celestial bodies with luster to preset magnitude and detection of potentially dangerous celestial bodies (asteroids and comets) over 100 m in size revealed at about 150,000,000 km and more at the time of their approach to the Earth of one month and more. Space system comprises space craft with one or several telescopes and continuous radio communication of surface stations located in geostationary or near geosynchronous orbit and equipped with scanning means and onboard data processing means. Besides, it includes surface control means and data reception and processing means.

EFFECT: extendable space system configuration.

24 cl, 8 dwg

Description

The present invention relates to space technology.

The aim of the invention is the detection and observation of celestial objects, as well as increasing the efficiency of detection of dangerous celestial bodies (asteroids and comets) of 100 m or more in size, including those observed for the first time, determining the degree of their danger to the Earth and issuing a warning about upcoming time and place of their collision with the Earth for such a time that is sufficient to prevent a collision and / or take measures to reduce damage.

The invention includes a method for viewing the celestial sphere for detecting celestial objects with a brightness of up to 25 magnitude and a space system of one or more spacecraft (SC) in near-earth orbits capable of implementing the proposed method for viewing the celestial sphere and observe these celestial objects.

Known spacecraft that conduct observations of celestial objects (stars, planets, comets and asteroids), which can be considered as analogues of the present invention.

For more than 20 years, the Hubble Space Telescope has been observing from a low circular orbit [1]. This telescope detected a large number of asteroids and observed the comet Shoemaker-Levy on Jupiter in 1994.

In 2003, the Spitzer space telescope [2], designed for astrophysical observations, was launched into the heliocentric orbit. The main mirror of the telescope has a size of 0.85 m. The telescope includes three channels operating in different parts of the infrared range. This spacecraft moves in Earth orbit at a distance of about 0.01 astronomical units behind the Earth. Spitzer is not designed to observe asteroids, but they are noticeable in images taken simultaneously in different parts of the spectrum.

Since 1997, the SOHO space observatory has been conducting observations [3], and since 2009, the WISE wide-angle infrared explorer [4], launched into polar orbit. On February 17, 2011, the WISE satellite was put into sleep mode.

There are also a number of other foreign space telescopes capable of observing asteroids. In addition, a number of projects have been developed (for example, Gaia [5], NEOSSat [6], Asteroid Finder [7]), which are intended, among other things, for observing asteroids from near-Earth circular orbits. The NEO Survey spacecraft [8], intended for the same purposes, will be launched into Venusian orbit or to the Lagrange points L1 or L2.

As the Russian analogue of the invention, one can consider the "Method of mapping the celestial sphere and the spacecraft for its implementation" [9]. The equipment of this spacecraft, along with the stars, is also capable of detecting asteroids with a brightness of up to 10th magnitude.

The disadvantage of almost all of the analogs described above is that they survey the entire celestial sphere for a period of several months or more, and therefore are unable to provide information on celestial bodies that have not been previously observed and threaten a collision with the Earth in the operational mode, which makes it possible to prevent a collision or minimize damage From him.

As a prototype, the space system for detecting and monitoring asteroids and a method for viewing the celestial sphere described in US patent [10] were adopted. The spacecraft of this system revolves in a circular low Earth orbit, for example, 770 km with a circulation period of about 100 minutes, that is, it makes 15 orbits in 1.04 days. The spacecraft is equipped with observation equipment with a field of view of 12 ° × 12 °, capable of deviating in the same plane (relative latitude) by an angle of approximately ± 85 ° relative to its zero position. The spacecraft is constantly oriented so that in the zero position the optical axis is directed along the local vertical upward from the Earth, and the plane of deviation of the optical axis is perpendicular to the orbit plane. Thus, in one revolution, the spacecraft makes one revolution around its axis perpendicular to the plane of the orbit, and its observation equipment scans an annular band 12 ° wide on the celestial sphere (in the zero position in latitude, the optical axis moves along the arc of a large circle, in the deviated position, along arcs of the corresponding small circles). At the beginning of each subsequent turn, the optical axis is moved to the next position in latitude, that is, it occupies one of 15 fixed angular positions, making a complete circular scan in one turn. This scanning scheme is shown in FIG. 1, which, along with FIG. 2, FIG. 3 and FIG. 4, is a copy of the illustration from the US patent. With such a scanning scheme, the entire celestial sphere is viewed approximately in a day, performing scans from number 1 to number 15 on successive turns.

A two-dimensional flat array of photodetectors with a size of 4096 × 4096 elements, corresponding to a field of view of 12 ° × 12 °, is placed in the focal plane of the observation equipment. Each element of this matrix corresponds to a field of view of size 10.5 "× 10.5".

With the above orientation, the angular velocity of the spacecraft is equal to the angular velocity of the orbital motion. Each point of the celestial sphere passes through a field of view with a width of 12 ° in at least 3.2 minutes, even in the extreme case when such a point lies in the plane of the orbit. For any point in the celestial sphere with a non-zero latitude falling into the scanning strip, the angular scanning speed decreases in proportion to the cosine of its latitude, and the time passing through the field of view increases accordingly, obviously exceeding 3.2 minutes. This circumstance makes it possible on the plane of the photodetector matrix, occupying one of 15 fixed latitude positions on the i-th scan, for each latitude of the observed point to assign two matrix elements symmetrically located relative to the vertical axis of the field of view, for which the interval of time passing through them is one and the same point in the celestial sphere is 3.2 min. The totality of these points on the photodetector two-dimensional matrix over the entire latitude range of this i-th scan forms two lines (two one-dimensional arrays of elements) that are not straight. The first of them, along the scan, is line A, and the second is line B shown in FIG. 2 (lines A1, B1 for a certain position of 101 KA in orbit and lines A2, B2 for its position 102 in 3.2 minutes). These lines are also shown in FIG. 3 and are indicated by scan number 1 with a dash (line A) and without a dash (line B). The set of elements corresponding to the lines A and B on the photodetector matrix is shown in Fig. 4 (positions 10 and 12).

The main idea of recognition by this system of close celestial objects that can be dangerous to the Earth is as follows. The signal from each element on line A, when scanning the moving first one, is stored for 3.2 minutes and at the moment of arrival of line B at the same points in the celestial sphere, the stored signals from the elements of line A are subtracted from the received signals of the corresponding elements of line B. If in this point of the celestial sphere, the signal has not changed (it does not matter if there is a star there or not), the result will be zero. If, in 3.2 minutes, the radiation source has shifted in the celestial sphere, after subtraction in the “old” and “new” points of the celestial sphere on which the object was projected, the signals from it will be saved and should be remembered and further processed to identify celestial bodies dangerous to the Earth . In this case, the parallactic displacement of a given celestial object is also measured. Declared in the prototype, the minimum diameter of a detectable dangerous celestial body moving towards the Earth is 50 m.

The prototype patent refers to devices located on a spacecraft and implementing the operations of forming the first and second images with a two-dimensional matrix, storing them for a while, subtracting one image from another to form the resulting image and transmit the resulting image to Earth. In addition, when forming images using a two-dimensional matrix, an additional device is used to turn on and off selected matrix elements forming lines A and B (pos. 10 and 12 in Fig. 4), which are selected on the matrix before each scan, depending on the latitude of this scan. The task of these lines is to provide the same time interval (for example, as indicated in the description of the prototype, 3.2 min) between the passage of the same points of the celestial sphere with the corresponding elements of the first and second lines.

The specified prototype has the following significant disadvantages, predetermined mainly by the claimed method of viewing the celestial sphere.

1. The angular velocity of movement along the celestial sphere of the projections of lines A and B is significantly different at different latitudes (from the maximum 2π / T _revolution at the "equator" to zero at latitudes + 90 ° and -90 °). This leads to different times of accumulation of signals from point radiation sources on the elements of the photodetector matrix, which leads to different detection ranges of celestial bodies of the same brightness.

2. The reading mode with a time delay and accumulation (WZN) is not used when interrogating elements of a two-dimensional matrix or two lines of optical photodetector elements, which allows to increase the detection range of celestial bodies.

3. The small guaranteed detection range of dangerous celestial bodies moving towards the Earth and having a diameter of not only 50 m, but also 100 m.

4. Loss of time during the inevitable scanning of blinding near-solar space.

5. There is no possibility of a repeated return to observation of a point in the celestial sphere with a newly discovered potentially dangerous celestial body after a desired arbitrary period of time, since the tact of the surveys is rigidly determined by the claimed survey method.

6. The design of the spacecraft is complicated by the presence of a rotary device that moves the optical axis of the observation equipment relative to the spacecraft body from scan to scan in latitude.

The technical result of the invention consists in a new method for scanning the celestial sphere with observation equipment in full large circles or in sections formed by parts of large circles by rotating the spacecraft body with a given constant speed, different for different parts of the sky. This allows you to register all celestial objects with a brightness of up to 25 magnitude and to identify dangerous celestial bodies (asteroids and comets) of 100 m or more in size, detected at a distance from the Earth of ~ 150 million km or more, at which the time of their approach to the Earth is 1 month or more.

The technical result of the invention also lies in the new construction of a space system, including a spacecraft placed in geosynchronous or close to it geosynchronous orbit with one or more telescopes with photodetector arrays operating in the mode with a time delay and accumulation, scanning support tools according to the proposed method, on-board information processing complex and continuous radio communication with ground control points, receiving and processing inf rmatsii within the system.

The proposed method and system ensures the detection of first-observed asteroids of 100 m or more in size, moving from anywhere in the celestial sphere along the trajectory of falling into the Earth, and issuing a warning about this in the extreme case at least 20 days before the collision. It also provides replenishment of catalogs of celestial objects with objects with a brilliance no weaker than 23 ... 25 magnitude with regular updating of parameters recorded in catalogs of objects.

The invention aims at detecting, observing and measuring the parameters of celestial objects during the survey of areas covering the entire celestial sphere or part thereof, with registration of all celestial objects with brilliance up to the 25th magnitude, and increasing the efficiency of detection of celestial bodies of the solar system (asteroids and comets) measuring 100 m or more, including those observed for the first time, determining the degree of their danger to the Earth and issuing a warning about the upcoming time and place of their collision with the Earth for such a time that is sufficient for I avoid a collision and / or the adoption of measures to reduce the damage caused.

The invention includes a method for viewing the celestial sphere from a spacecraft and a space system that implements this method.

The proposed method for scanning the celestial sphere can be used to solve various scientific and applied problems, including the early detection of asteroids and comets that are dangerous for the Earth. A characteristic property of the proposed scanning method is the uniform movement of the field of view of the observation equipment (AN) in the scanning mode along trajectories that are complete large circles in the celestial sphere or parts of such circles.

Such a choice of scanning paths makes it possible to minimize blurry images of the sky and increase the signal-to-noise ratio, which, in turn, leads to an increase in the penetrating ability of AN. Only when scanning in large circles do the velocities of moving images of celestial objects across the field of view differ minimally and are almost the same even if telescopes with sufficiently wide fields of view are used as part of the AN. Such a scan is easy to carry out with a fixed telescope on a uniformly rotating spacecraft.

A special case of the proposed method, in which scanning is carried out over a complete large circle, can be used for high-precision astrometric measurements, where the completeness of the circle allows you to close the system of equations in one scan. Moreover, the entire review may not cover the whole sky, but may consist of circular scans containing only reference objects, for example, optical quasars. When exploring the plane of the Galaxy, the Milky Way, such circular scans can also cover only part of the sky.

The proposed method for uniform scanning along trajectories that are parts of large circles can be used for many scientific tasks, for example, in the study of variable stars, photometry of all stars in the sky, the study of objects of the solar system,

Of particular interest is the scanning of the celestial sphere, in which for each part of the sky its own exposure time of objects is selected and, therefore, its own scanning speed. It is advisable to use such a scan to solve the problem of detecting bodies of the solar system (asteroids and comets) dangerous for the Earth, for example, 100 m or more, including those observed for the first time, to determine the degree of their danger to the Earth and to issue a warning about their upcoming time and place of collision with the Earth for such a time that is sufficient to prevent a collision and / or take measures to reduce damage (for example, 2-3 weeks before a collision).

The need to use scanning at different speeds in different parts of the celestial sphere is related to the difference in the times of approaching the collision point for dangerous bodies moving after or towards the Earth, and therefore located at different distances from the Earth and having different brightness at the same time from detection to collision.

A method for viewing the celestial sphere to detect celestial bodies dangerous to the Earth includes dividing it into a number of sections. The dimensions of the celestial sphere selected in this case can be, for example, 30 ° × 60 ° and 30 ° × 30 °. Such areas should, with some overlap, completely cover the entire celestial sphere, with the exception of the area around the Sun with an angular radius ranging from 15 ° to 30 °, determined by the shielding capabilities of the hood.

In the near-solar region, observation of weak celestial objects is impossible, and for the corresponding calendar interval this region of the celestial sphere is excluded from the scanning process. However, as the sun moves along the ecliptic, the ground-based control complex covers with new areas of the survey the areas of the celestial sphere freed from exposure.

The review of each section is carried out by scanning the observation equipment fixed on the spacecraft by rotating the spacecraft. The angular width of the scanning strip corresponds to the width of the field of view of the telescope or the width of the combined field of view in the case of installing two or more telescopes on the spacecraft. The axis of the SC rotation of the spacecraft is perpendicular to the central axis of the combined field of view. As a result, the center line of the scan band is always part of a large circle of the celestial sphere. Each of the aforementioned sections of the celestial sphere is covered by several scanning bands (scans) during the scanning rotation of the spacecraft with an assigned angular velocity constant for this section. The scans touch and partially overlap each other in the direction transverse to the scanning direction. In most areas, the continuation of the central lines of the scans, which are large circles, pass through the center of the Sun (Fig. 5). At the end of each scan, the spacecraft is reoriented to the adjacent scan and the scan direction is reversed at the boundary of the survey area.

Figure 5 shows a KA observer 1 located in the center of the celestial sphere, the center of the Sun 2, a near-solar region 3 with an angular radius of 30 °, the ecliptic plane 4, a large circle 5, whose plane t passes through the spacecraft perpendicular to the line of the spacecraft - the Sun, and also five scans 6 ... 10, forming a selected portion of the survey of the celestial sphere measuring 30 ° × 60 °. The width of each scan strip in FIG. 5 is taken to be 6 °, and the strip length is 60 °. Bold lines show the scan strips of scans 6, 8, 10. The start and end borders of scans 7 and 9 are indicated by the temples, and the center lines of the scan strips are indicated by dashed lines. The dotted line also shows the anti-solar region 11 of the celestial sphere with an angular radius of 30 °, the center of which 12 is diametrically opposite the center of the Sun 2.

This orientation of the scans, as can be seen from figure 5, allows with a minimum overlap to "outline" the avoided circular region of flare around the Sun. However, when reviewing the antisolar region, conducting all scans through the center of this region leads to unreasonably large overlap and a corresponding loss of time. Therefore, in two or three areas covering the antisolar region, the central lines of the scans, that is, large circles, must pass through any (but a single) point of the celestial sphere 85 ° ... 95 ° away from the Sun (Fig. 6). In this case, the antisolar region is covered by "parallel" scans with minimal unnecessary overlap. Figure 6 also shows the possibility of reducing the length of individual scans in this area.

Figure 6 shows the celestial sphere from the side opposite to the Sun 2, with a highlighted portion of the observation of the celestial sphere measuring 30 ° × 60 °, covering half of the antisolar region. All points of the great circle 5 of the celestial sphere, the plane of which is perpendicular to the line of the spacecraft - the Sun, are 90 ° away from the Sun. Therefore, through any point 13 selected on this large circle, it is possible to draw the center lines of scans 14 ... 18, shown by a dotted line. Through the same point, the central lines of all scans should be drawn, forming another (not shown in FIG. 6) similarly selected viewing section, docked to the first section and covering the second half of the anti-solar region. In the lower part of Fig.6 is a view of the selected area from the axis 19, on which the borders of the scans 14, 16, 18 are indicated by bold lines, and the borders of the scans 15 and 17 are shown by the arms. With a scan bandwidth of 6 ° and a length of 60 °, the overlap of adjacent scans at their ends reaches ± 0.4 °.

For each specific area of the celestial sphere, its own constant scanning speed is selected, which is determined by the following factors.

one). The minimum time from the first detection of a celestial body to its impact on the Earth is taken to be equal to one month, which can be considered sufficient to accurately measure its motion parameters, to identify its degree of danger and to take subsequent measures to prevent a collision and / or minimize damage.

The celestial body of the solar system, in the extreme case, moving along a parabolic trajectory towards the Earth with a maximum speed of 42 km / s at the point of collision with the Earth [11, p. 257], which has its own orbital speed of 30 km / s [11, p. 394] collides with the Earth at a speed of 72 km / s. The estimated range to such a celestial body, corresponding to the approximation time of one month, is ~ 1 astronomical unit (~ 150 million km). At this range, the spacecraft equipment should detect celestial bodies of 100 m in size. If the size of a celestial body is 200 ... 500 m, its detection range increases to 2 AU and more. In this case, the estimated time of approach increases to two months or more.

With a celestial body size of 100 m and an albedo value of 0.2, its calculated brightness at a distance of 1 a.u. corresponds to 25 magnitude. The detection of such a weak radiation source when taking into account the background level in a given section of the celestial sphere requires an appropriate signal accumulation time. As calculations show, with the characteristics of the telescope and its photodetectors that are actually possible at present, the signal accumulation time should be, for example, 180 s. The telescope parameters and the required signal accumulation time determine the scanning speed of a given section of the celestial sphere.

2). Background radiation is different in different parts of the celestial sphere (for example, the Milky Way, the zodiacal light), so the scanning speed should be reduced with a high background level in this area.

For each review cycle of the full celestial sphere at the ground control, reception and information processing center (NITS), calculations are made to divide the celestial sphere into separate sections, determine the sequence of their review and select the scanning speed for each section of the review, as well as the start times of each scan and spacecraft orientation parameters at the initial moments of scans.

The sequence of the review of the aforementioned sections of the celestial sphere is determined by the size of the time interval through which it is necessary to perform a repeated (or, for example, triple) review of each section to determine, with a given accuracy, the parameters of motion of celestial bodies and the degree of their danger.

The obtained calculation results are summarized in an ordered sequence of parameters for viewing the plots on the cycle of viewing the celestial sphere and transferred to the SC in the scanning control complex as a program for viewing the celestial sphere for the corresponding time interval.

The magnitude of the time intervals between repeated surveys of the plots and the multiplicity of surveys can be determined at the initial stage of the functioning of the space system according to the results of observations of the celestial sphere. Too close in time the observation sessions of the same section do not allow determining the motion parameters of the observed celestial body with the necessary accuracy, and with too long time intervals there is a danger of "confusion" of several moving celestial bodies. The viewing time of one site with different versions of the design of the photodetector, exposure time and size of the site can be, for example, from 0.5 hours to 6 ... 10 hours. Therefore, a group of sections is selected for which the sum of the times of their review is approximately equal to the duration of a given (desired) interval between reviews of the same section. If necessary, this review can be repeated as many times as necessary, after which they proceed to review the next group of sections of the celestial sphere. This process is repeated until the celestial sphere is completely covered, with the exception of the near-solar region, which may take several days (for example, about 3 days with a single review of the celestial sphere and 10 ... 11 days with a triple review).

Thus, if a newly discovered celestial body after three times of informational contact with it and measuring its motion parameters is qualified with a given probability as dangerous to the Earth, from the above minimum flight time in the limiting case of one month after the first detection of the celestial body, about 20 days remain to parry identified threats and / or measures to minimize damage.

When qualifying a newly discovered celestial body as potentially dangerous in the control complex of the NLTPL, it is possible to transfer the spacecraft to the continuous tracking mode of this celestial body. For this, a reduced viewing area is assigned, consisting, for example, of one short scan 3 ° ... 6 ° long. The simultaneous approach to Earth of two new celestial bodies, assessed as potentially dangerous, is extremely unlikely. Therefore, in the event of the discovery of a new potentially dangerous celestial body, the regular review of the entire celestial sphere is interrupted and only the reduced portion of the celestial sphere containing this dangerous celestial body is monitored until the qualification for the threat of collision with the Earth is withdrawn (or until the moment of collision). After that, a return is made to the scheme of regular review of the celestial sphere.

With the current level of technology, the detection of radiation sources of 23 ... 25th magnitude at a scanning speed of the celestial sphere of up to 0.10 deg / s with a telescope mounted on a spacecraft, is possible with a photodetector (FPU), consisting of charge-sensitive photosensitive matrix devices (MPS) with reading the signal from the elements of the MPS in the mode with a time delay and accumulation (WZN) [12].

The main photodetector (OFPU) of the monitoring equipment is a two-dimensional orthogonal mosaic, consisting of MPZS. The WZN mode is realized by transferring charges in the columns of the MPZS elements, which can be performed both in the forward and in the reverse direction with the speed of movement of the sky image. At the same time, the spacecraft is continuously oriented so that the columns of the MES in the mosaic and the columns of the elements in the MES themselves are parallel to the specified scanning direction.

To detect a signal from celestial bodies of the 25th magnitude, a signal accumulation time (exposure time) of at least several tens of seconds is required. This time is the sum of the transit times of the image of the celestial body over all the MPSS of the OFPU mosaic column along the image motion path. Typical accumulation times can be taken, for example, 30 s, 60 s, 120 s, 180 s. In accordance with these accumulation times, which depend on the position of the viewing area in the celestial sphere, and the mosaic parameters of the MPPS OFPU, the scanning speeds calculated for the spacecraft are calculated.

To observe celestial objects with a brightness lower than the 25th magnitude, an exposure time of more than 180 s should be used, which is achieved by a corresponding decrease in the angular scanning speed.

The image of a point source of radiation during the scanning process must pass through the same column of elements in each corresponding MES. The angular size of the field of view of the element MPS is, for example, 0.25 "× 0.25". In this case, the transverse movement of the image of the radiation source should be kept within, for example, one quarter of the width of one given column of MPS elements. To implement such a scan, high accuracy of measuring the current direction of motion of fixed stars in the telescope field of view is required. In addition, to synchronize the line-by-line reading of the signal with the actual transitions of the images of fixed stars in each successive line of MPS elements, continuous accurate measurement of the value of the current actual angular velocity of the stars is necessary.

To perform these functions, high-precision stellar sensors (ZD) are placed next to the mosaic of the MPZS OFPU, which are special photosensitive MPZS with frame transfer, which produce measurement results with a frequency, for example, 10 Hz. Frame transfer MPS consists of a photosensitive section and a storage section. In the photosensitive section, the image is exposed and the frame is formed. The exposed frame is transferred to the photosensitive storage section, in which it is read.

The set of MPSS of star sensors is hereinafter referred to as FPU of star sensors (FPUZD). An example of a possible mutual arrangement of the mosaic of the MPSS OFPU and special MPSS of star sensors is shown in Fig. 7. It shows the calculated field of view 20 of the telescope with the main photodetector 21 and special MPSS of the star sensors 23. OFPU is a rectangular mosaic of MPSS, forming columns and rows, oriented so that the columns of the MPSS of the mosaic (and the columns of elements in each MPS) are parallel estimated direction 22 of the reversed scan. A somewhat reduced circular region 24 is distinguished in the field of view, within which the image distortion does not exceed a value acceptable to ensure a given measurement accuracy of stellar sensors. Star sensors are placed in the area 24 outside the boundaries of OFPU 21 with the same orientation of the columns of the MPS elements along the scanning direction.

The assembly of OFPU and FPUZD is placed on a movable rigid base so that the columns of the MPZS elements of both FPUs are parallel, and the photodetector surfaces of the MPZS OFPU and FPUZD form a single plane. The rigidity of the base ensures the invariance of the mutual geometric position of all the MPS of both FPUs. This base is mounted on a mechanical base moving device (MUPO), which provides small fast rotations in one angular direction and displacements in two linear coordinates in the focal plane of the telescope for the indicated plane of the base. This parries the current deviations of the image movement from the uniform and parallel to the columns of the MPZS, that is, keeping the passage of the image of the celestial object within the specified limits relative to the columns of the elements of the MPZS for both FPU. It is also possible to increase the number of degrees of freedom of motion of the MUPO to three linear displacements and three angular rotations; additional degrees of freedom may be useful for focusing and adjusting the telescope optical system.

According to information from stellar sensors, current discrepancies of the actual and required vectors of the angular velocity of stars moving along the photodetector matrices are calculated. These mismatches may contain both low-frequency and high-frequency components. The low-frequency component is generated by the residual error in the spacecraft’s orientation and stabilization system performing the specified angular motion of the spacecraft’s hull around its center of mass. The high-frequency component, having a small amplitude, may be the result of vibrations.

The indicated small discrepancies (errors) are parried by the MUPO by commands from the control unit of the mechanical device (BUMU), the input of which receives information about the calculated discrepancies.

Based on the above data, an assessment is made of the comparative detection range of the same celestial body by the prototype and the invention. In this assessment, we proceed from the following provisions:

- the phase angle of the spacecraft - the celestial body - the sun when comparing the detection range is taken equal to zero;

- the diameter of the entrance pupil of the telescopes is the same for both considered space systems;

- the detecting ability of photodetectors in both systems under consideration is the same.

Let d be the diameter of the celestial body, D be the observation range, T be the exposure time, that is, receive the radiation of the celestial body during scanning, k, k ₁ , k ₂ be the proportionality coefficients that are the same for both space systems.

The radiation power of a celestial body (i.e., the radiation power M ₁ ) is proportional to its area:

M ₁ = k ₁ d ²

The power of the received signal M ₂ from the celestial body is inversely proportional to the square of its range:

$${\mathrm{<figure-callout\; id="2"\; label="M"\; filenames="00000008.png,00000010.png"\; state="\{\{state\}\}">M</figure-callout>}}_2=\frac{k_2}{{\mathrm{<figure-callout\; id="2"\; label="D"\; filenames="00000008.png,00000010.png"\; state="\{\{state\}\}">D</figure-callout>}}^2}\cdot M_{\mathrm{one}}$$

The energy of radiation E received by the receiving device is proportional to the exposure time:

E = M ₂ · T

Thus, the energy received by the photodetector from the celestial body and used in the development of a signal about the detection of this body has the form

, k=k₁·k₂. $$E=k{\left(\frac{d}{D}\right)}^2\cdot T$$

, K = k ₁ · k _2.

In the prototype, the exposure time is the transit time of the image of a point source of radiation through an element of the photodetector matrix having an angular field of view of 10.5 ". For each scan on the photodetector matrix, lines A and B intersect with the image of a celestial body formed from such elements. The prototype has an angular the speed of movement of the field of view of the element of the photodetector matrix in the celestial sphere ω depends on the angular velocity of the scanning rotation of the spacecraft ω ₀ and the conditional latitude of the field of view of the element Ш:

ω = ω ₀

The exposure time T of this element having an angular size ε in the scanning direction:

$$T=\frac{\epsilon }{\omega }$$

The angular velocity of the scanning rotation of the spacecraft ω ₀ is equal to one revolution in 100 minutes, that is, ω ₀ = 216 "/ s.

In the worst case, W = 0, the exposure time of the prototype is 0.05 s. At W = 60 ° it increases to 0.10 s. Since 86.6% of the celestial sphere lies in the range of latitudes from -60 ° to + 60 °, in further calculations we take the exposure time for the prototype as 0.10 s with a significant margin in favor of the prototype in this latitude region.

Consider the resulting expression in modified form:

$$\frac{E}{k}={\left(\frac{d}{D}\right)}^2\cdot T$$

The left side contains the same radiation energy E received from the observed celestial body and necessary to make a decision on its detection for each compared system, as well as the coefficient k, which is assumed to be the same for these systems. The right side contains the detection parameters obtained for the proposed invention, in which the exposure T = 180 s is assigned for the most dangerous parts of the celestial sphere. Moreover, for a celestial body with a diameter of 100 m, the detection range is 150 million km.

For the prototype, we take the exposure T = 0.10 s and a diameter of 50 m. Due to the equality of the left parts of the last expression for the prototype and the present invention, we obtain the expression

$${\left(\frac{\mathrm{one\; hundred}m}{150mln.\mathrm{to}m}\right)}^2\cdot 180\mathrm{from}={\left(\frac{\mathrm{fifty}m}{Dmln.\mathrm{to}m}\right)}^2\cdot 0.1\mathrm{from}$$

From here follows the detection range of a celestial body with a diameter of 50 m for the prototype in the most dangerous situations:

$$D=\sqrt{\frac{0.1\mathrm{from}}{180\mathrm{from}}}\cdot \frac{\mathrm{fifty}m}{\mathrm{one\; hundred}m}\cdot 150mln.\mathrm{to}m\approx \mathrm{1,768}mln.\mathrm{to}m$$

This range is approximately 85 times less than that of the present invention.

If we take for the prototype the diameter of the detected celestial body is 100 m, the detection range is doubled, but remains ~ 42 times less than that of the present invention.

With sufficient accuracy for the assessment, we consider the warning time proportional to the detection range.

With an increased detection range of a dangerous celestial body, the warning time for the moment of the expected collision of the detected celestial body with the Earth also increases, which indicates a significant advantage of the present invention over the prototype.

A space system that implements the above-described method of observing the celestial sphere includes a spacecraft with one or more telescopes, a ground control, reception and information processing center (NLTPL), an additional information reception and processing center (PLOI) and an information-analytical center (IAC), shown in FIG. It is also possible to expand the space system by introducing additional spacecraft into it and the corresponding number of NPPOI and PLOI.

The spacecraft is launched into a geostationary orbit or into a geosynchronous elliptical orbit with a revolution period of ~ 86164 s, which has an approximately constant path (ephemeris) on the Earth's surface or, in the case of GSO, a constant standing point. From these orbits, continuous radio communication with NPPOI and PPOI is provided. Ground points NNPOI and POI should be deployed at sufficiently close geographical points so that they simultaneously fall within the narrow radiation pattern of a highly directional antenna (OHA) of the spacecraft pointing to the midpoint between them. The spacecraft standing point on the GSO or the path of an elliptical geosynchronous orbit should be close to the meridians of the NLTPL and the LARP.

The following main functionally isolated devices are installed on the spacecraft: observation equipment, a control unit and information processing unit of the main photodetector device (BUOFPU), a control unit and information processing unit for photodetector devices of star sensors (BUZD), a control unit for a mechanical device (BUMU), a motion control system and Navigation (VESS), with the help of which the given orientation of the spacecraft at the beginning of each scan and the subsequent scanning rotation of the spacecraft around its center of mass with a given Glov speed scanning control complex (LCPs), two-way radios, antenna-feeder system.

On Fig shows a structural diagram of a space system for viewing the celestial sphere for the detection of celestial objects. The observation equipment 26 of the spacecraft 25 includes a telescope 28 with a main photodetector (OFPU) 31 and a photodetector of star sensors (FPUZD) 32, as well as a mechanical device for moving the base (MUPO) 29 with a movable base 30, on which both FPU are mounted.

At the input of the optical system of the telescope, radiation comes from celestial objects, some of which are projected onto the MES of the main FPU 31, and the other part is projected onto the MES of the star sensors of the FPU 32.

OFPU 31 is a rectangular mosaic of MPZS placed in the focal plane of the telescope, for example, 20 × 20 MPZS, which form the rows and columns of the mosaic. The format of each MPL is, for example, 2048 × 2048 elements. The size of the MPSS line of the OFPU mosaic characterizes the width of the field of view of the telescope, that is, the width of its scanning strip.

The OFPU parameters and exposure time provide registration of signals from all point radiation sources up to 25 magnitude with a maximum exposure time. The analog video signals from all the outputs of the MPS of the main FPU are fed to the input of the OFPU control unit and information processing unit (BUOFPU) 34. The input of the OFPU 31 from the output of the BUOFPU 34 is supplied with clock pulses of charge transfer in the elements of the MPZS columns, as well as clock pulses of reading information along the lines of the frame in output registers MPZS OFPU.

FPUZD 32 consists of a set of, for example, 20 stellar sensors, which are located outside OFPU near its border and near the edge of the telescope's field of view. Each star sensor has a detecting ability, in which the required number (for example, 80) of navigation stars is recorded.

MUPO 29 parries the high-frequency small components of the mismatch of the actual and required vectors of the angular velocity of the image of celestial objects along photodetector matrices. At MUPO from the control unit of the mechanical device (BUMU) 27 commands are issued to control the position of the base 30 with the assembly OFPU 31 and FPUZD 32, ensuring the passage of images of celestial objects within specified limits along the columns of the elements of the MPS.

The control unit and the integrated processing of information of the main photodetector (BUOFPU) 34 receives analog video signals from all outputs of the MPS of the main FPU 31. The electrical circuit of the device for reading and preprocessing video signals in this unit reads out the accumulated charges line-by-line, digitizes them and preprocesses, including the correction of heterogeneity the sensitivity of each MES and subtraction of the background, which is formed by both the dark current of the MES and the emission of unresolved objects to the sky natural sphere. Preliminary processing also extracts images of objects in frames from each MPS, their verification and rejection of interference, as well as summing the signal and calculating coordinates for detected objects that have passed through the entire set of MSC elements (the image of one object can immediately hit several neighboring MSC elements, moreover differently for different MPZs). The value of the total accumulated signal from each observed object is proportional to the exposure time, that is, to the net image transit time along all the MSSs that make up one mosaic column (excluding the image transit time along technological gaps between the MSSs).

The input BUUFPU 34 receives from the block BUZD 35 information about the low-frequency component of the change in the current velocity along the columns of the elements of the MPSS images of fixed stars on the focal plane. According to these data, in BUOFPU 34, the current values of the charge transfer clock frequency in the columns of the MPZS elements and the clock frequency of reading information in the output registers of the MPZS OFPU 31 are calculated, matching the moments of the polling of the elements with moving images of fixed stars, which prevents blurring of images with imperfect scanning movement of the case KA.

The special electric circuit included in BUOFPU 34 generates clock pulses in accordance with the calculated frequency for transferring charges and reading the signals of MPPS OFPU 31. BUOFPU 34 gives these pulses to the input of OFPU 31. Based on the totality of information received from OFPU 31 and from BUZD 35, the block BUOFPU 34 determines the current values of the celestial angular coordinates and brightness of all observed objects, encodes them and transmits them in real time to the input of the transmitter 38 or, if necessary, to the buffer memory (not shown in Fig. 8).

BUZD 35 reads from the output of the FPUZD 32, that is, from the output of each ZD, frames of the image of the starry sky with navigation stars. The received frames are digitized and processed to identify stars moving in successive frames. Then, the deviations of the measured coordinates of the navigation stars from their calculated (predicted) positions are calculated. Based on these data, the current values of the actual angular velocity and scanning direction are determined. In accordance with them, the clock frequency of the WZN mode in the photosensitive sections of the MPSS of stellar sensors is calculated, as well as the clock frequency of reading and the frame transfer frequency. The generated corresponding clock pulses from the first output of the BUZD 35 are transmitted to the FPUZD 32.

The control unit for the mechanical device BUMU 27 from the second output of the BUZD 35 receives control signals about the desired spatial position of the movable base 30 with the assembly OFPU 31 and FPUZD 32. The control commands for actuating actuators are generated by them, which are issued to the mechanical device MUPO 29.

The current values of the low-frequency component of the error in direction and scanning speed from the third output of the BUZD 35 are fed to the input of the SUDN to parry them while controlling the scanning angular motion of the spacecraft hull. In addition, from the fourth output of the BUZD 35, the current actual values of the direction and scanning speed are output to the input of the BUOFPU 34.

The management of scanning the celestial sphere is organized as follows. The control complex 48, which is part of NLTPL 46, calculates the initial data for the scanning program for the upcoming next cycle of the review of the celestial sphere. The review program includes moments of the beginning of the review of each section of the celestial sphere, the initial orientation parameters corresponding to them, and the scanning speed of this section. For each part of the celestial sphere, the program contains the start time of each scan, the orientation parameters of the spacecraft at the beginning of the scan, and the length of the scan. The order of the review of sites is made in such a way that the time interval between re-reviews of the same sections of the celestial sphere approximately corresponds to the desired described above. This also takes into account the selected number of returns to the same site. Thus, the review cycle of the entire celestial sphere is a sequence of surveys of the plots that completely covers the celestial sphere, with the exception of the near-solar region, and obtaining information frames corresponding to these plots with information containing the image of the sky. At the same time, a review of each section is carried out taking into account the required multiplicity at the desired time intervals. An array of initial data for a cycle of a full review of the celestial sphere is transmitted from a ground station to the spacecraft at a time or in parts as the relevant parts of the program are completed.

The scanning control complex (SCC) 36 is a computing device that calculates and provides, with a given step in real time, parameters that specify the required current orientation of the spacecraft body during the scanning process. KUS 36 receives from the output of the receiver 39 the initial command information about the viewing order of the celestial sphere. This information contains the initial data on each surveyed area (its size, position on the celestial sphere, the required scanning speed, etc.) recorded in the order of the required sequence of the survey sites in the current review cycle of the entire celestial sphere. The results of calculations of the required orientation of the spacecraft at each calculation step are output from the output of the control panel 36 to the input of the COURT 33.

In addition, at each calculation step, the control panel calculates in the inertial coordinate system the parameters of the vector directed from the spacecraft to the mid-geographical point between the NLBID and the POI, and then recalculates them into the associated coordinate system of the spacecraft with the orientation corresponding to the current scanning position. Based on this calculation, the control panel determines which of the SHE contains the given vector in its working area and which angles of rotation of the drive of this SHE should be worked out at a given moment in order to align the axis of the SHE pattern with the said vector. This command information from the output of the control system 36 is issued to the drive control unit ONA 41.

The motion control and navigation system (VESS) 33 performs a given orientation of the spacecraft hull during scanning, transitions to an adjacent scan or to an overview of the next section of the celestial sphere. In the scanning mode, from the output of the control system 36 to the input of the SUDN 33 the parameters of the current set orientation are received with an agreed time step. In the reorientation mode, from the output of the KUS 36 to the input of the SUDN 33 the values of the time of the end of the reorientation and the values of the parameters of the required final orientation and the angular velocity vector of the spacecraft to start the next scan are fed. In addition, the input of the SUDN 33 from the output of the BUZD 35 in the scanning mode receives the current values of the low-frequency component of the measured error in the direction and scanning speed relative to their specified values. The result of the work of the SUDN 33 is the current orientation of the axes of the associated spacecraft coordinate system in the scanning and reorientation modes.

The target output information of the spacecraft is a stream of measured angular coordinates and brilliance of all registered (detected) point sources of radiation in digital form with time stamps, as well as signals of the mismatch of speed and direction of scanning from the BUZD. This data from the output of the BUOFPU 34 (or, if necessary, from the buffer memory) is transmitted to the transmitter 38 of the transmitting and receiving equipment 37 and transmitted through the ONA 43 of the antenna-feeder system 40 to the software 45 and to the non-standard program 46.

At the point of reception and processing of information (PPOI) 45 and in the computer complex for information processing 47 of the ground control point, reception and processing of information (NPPOI) 46, parallel and independently, information is continuously received via the radio channel from the spacecraft about the observed celestial objects. This information is compared with information from stellar catalogs and catalogs of the ephemeris of the solar system bodies. In the case of identification of radiation sources received from spacecraft and located in catalogs, it is possible to refine data on objects and bodies. For newly obtained and not identified with the radiation sources catalogs, further information is accumulated, the motion parameters of celestial bodies are refined, and their classification as potentially dangerous or non-hazardous.

NPPOI 46 exchanges the information received and processed with PPOI 45. NPPOI 46 also issues its own and transit (issued PLOI) information to the information-analytical center (IAC) 49 and receives from IAC 49 the relevant information. In addition, NLPIP 46 provides typical consistent information to external subscribers 50 that are not part of the described space system, and receives similar information from them.

NPPOI 46 through transmitters and antennas (not shown in Fig. 8) through a radio channel transmits to the spacecraft a scan program developed by its control complex 48. On the spacecraft, this command-program information is received by one or more antennas with a wide radiation pattern (MNA ) 44 connected to the receiver 39. The received command and program information from the output of the receiver is fed to the input of the scanning control complex (SCC) 36.

The present invention is intended for the detection and observation of celestial objects - stars, galaxies, quasars and bodies of the solar system, especially asteroids and comets, dangerous to the Earth.

The application of the proposed method for the review of the celestial sphere and the space system that implements this method allows for the first time to solve the problem of detecting (not less than 30 days) early celestial bodies with a diameter of 100 m or more that are on the trajectories of collision with the Earth in less than 20 days, information about the upcoming collision of a detected celestial body with the Earth.

Application of the aforementioned method and system also makes it possible to solve the problem of recording practically all celestial objects on the celestial sphere with a brightness of up to 25 magnitude with regular updating of information about their position and brightness with an interval of how many days.

From the foregoing, it follows that the proposed technical solutions have an advantage over the known methods of viewing the celestial sphere and space means in solving the problem of operational warning of an asteroid-comet hazard and the task of registering celestial objects with a brightness of up to 25 magnitude with regular updating of information about their position and brilliance.

Information sources

1.http // ru.wikipedia.org / wiki / Hubble.

2. http // ru.wikipedia.org / wiki / Spitzer.

3.http // ru.wikipedia.org / wiki / SOHO.

4.http: //wise.ssl.berkeley.edu/.

5.http // ru.wikipedia.org / wiki / Gaia.

6.http: //www.neossat.ca/.

7. http://www.dlr.de/pf/en/desktopdefault.aspx/tabid-174/319_read-18911/ (Asteroid Finder Project Asteroid Finder).

8. http // en.wikipedia.org / wiki / Large Sinoptic Survey Telescope.

9. A method for mapping the celestial sphere and a spacecraft for its implementation (RF patent No. 2014252).

10. Space-based asteroid detection and monitoring system (Space-based asteroid detection and monitoring system, US patent No. 5, 512, 743, Apr. 30.1996).

11.P.G. Kulikovsky. Handbook of astronomy lovers. / M .: Fizmatlit. 1971.

12. S.B. Howell. Handbook of CCD Astronomy / New York: Cambridge University Press. 2006. P. 96.

Claims (24)

1. A method for viewing the celestial sphere from a spacecraft (SC) for detecting celestial objects by observation equipment placed on the SC and creating images of celestial objects, which consists in alternately obtaining images of sections of the celestial sphere by observation equipment (AN), characterized in that the celestial sphere is surveyed from a spacecraft launched into a geosynchronous or close to it geosynchronous orbit, the coordinates and brightness of the observed celestial objects are determined by scanning the celestial sphere by rotating the spacecraft with starting from any assigned point, an arc of a given length is described in a predetermined direction on the celestial sphere with a constant angular velocity around an axis perpendicular to the central axis of the field of view of the AN, and the central line of the scanning strip, the angular width of which is determined by the width of the AN field of view, is part of a large circle of spheres, and at the end of a given scanning strip, they begin to describe the next arc of the big circle, the starting point, the direction and length of which is chosen so that the sky the scope of many scans one or more times cover the entire celestial sphere, or part of it. 2. The method according to claim 1, characterized in that the scanning is carried out in full large circles of the celestial sphere until returning to the starting point. 3. The method according to claim 1, characterized in that the scanning of various limited length sections of large circles of the celestial sphere is carried out with different constant speeds determined by the specified exposure times required to detect celestial bodies in the resulting images. 4. The method according to claim 2, characterized in that the scanning of large circles of the celestial sphere is carried out with different constant speeds determined by the specified exposure times required to detect celestial bodies in the obtained images. 5. The method according to claim 3, characterized in that the entire celestial sphere is surveyed over selected areas of the celestial sphere covered by several scans touching or partially overlapping each other in the direction transverse to the scanning direction, and at the end of each scan, the spacecraft is reoriented to transition to an adjacent scan and reverse the scan direction. 6. The method according to claim 5, characterized in that before starting the review cycle of the celestial sphere at the ground control point, receiving and processing information, calculations are made to divide the celestial sphere into separate sections covering the entire celestial sphere, determine the sequence of single surveys of each section and the speed scans at each site, and also calculate the temporal scanning parameters of each site and the orientation parameters of the spacecraft and transmit the results of calculations in the form of a work program to the spacecraft control system via the radio link nirovaniem spacecraft. 7. The method according to claim 6, characterized in that in the calculations for dividing the celestial sphere into separate sections, the sequence of multiple surveys of each section with their repeated scanning at a given time interval is determined. 8. The method according to claim 6, characterized in that when scanning the celestial sphere one or more selected sections are temporarily excluded from it, which are subsequently observed at predetermined time intervals. 9. The method according to claim 7, characterized in that when scanning the celestial sphere one or more selected sections are temporarily excluded from it, which are subsequently observed at predetermined time intervals. 10. The method according to claim 6, characterized in that the cycle of viewing the celestial sphere is interrupted, if necessary, and making observations that are not related to a systematic review of the celestial sphere, and then continue the interrupted cycle or begin a new cycle of viewing the celestial sphere. 11. The method according to claim 7, characterized in that the cycle of the review of the celestial sphere, if necessary, is interrupted and observations are not related to the systematic review of the celestial sphere, and then continue the interrupted cycle or begin a new cycle of the review of the celestial sphere. 12. The method according to claim 8, characterized in that the cycle of viewing the celestial sphere is interrupted, if necessary, and making observations that are not associated with a systematic review of the celestial sphere, and then continue the interrupted cycle or begin a new cycle of viewing the celestial sphere. 13. The method according to claim 9, characterized in that the cycle of viewing the celestial sphere is interrupted, if necessary, and making observations that are not associated with a systematic review of the celestial sphere, and then continue the interrupted cycle or begin a new cycle of viewing the celestial sphere. 14. The method according to any one of paragraphs. 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, characterized in that the celestial sphere is surveyed simultaneously from two or more spacecraft, and for each spacecraft, separate sections of the sky are distinguished spheres. 15. The method according to any one of claims 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, characterized in that from two or more spacecraft spaced in space, they simultaneously scan the same section of the celestial sphere and measure the parallactic displacements of celestial objects relative to the stars in the celestial sphere. 16. A space system for viewing the celestial sphere for detecting celestial objects, which implements methods for observing the celestial sphere with a spacecraft for detecting celestial objects, consisting of a spacecraft in Earth orbit, on which the equipment for observing celestial bodies and transmitting and transmitting radio equipment, a ground control center, and processing information (LITP) received from the spacecraft, and communication lines with subscribers of the system, characterized in that the spacecraft is placed in a geosynchronous or close to it geosynchronous orbit and is connected to the NLTPA continuous pit two-way radio communication, while on the spacecraft as part of the observation equipment, a telescope with a main photodetector (OFPU) is installed motionlessly relative to the spacecraft’s spacecraft, which is a mosaic of charge sensitive coupled photosensitive matrix devices (MPS), consisting of orthogonal rows and columns of elements and forming in a mosaic orthogonal columns and rows of the MPS, and a photodetector (FPU) of stellar sensors (FPUZD), in which each star sensor is a MPS with frame transfer, installed outside the OF Near to its border, with all OFPU MPZS and all star sensors mounted on a single movable rigid base so that the columns of the elements of all MPUs of both FPUs are parallel, and the photodetector surfaces of both FPUs form a single plane, and the movable base is placed on a mechanical device for moving the base ( MUPO), which provides such controlled small displacements and rotations of the base, in which the photosensitive flat surface of the MPZS OFPU and FPUZD is combined with the focal plane of the telescope, and the columns are an element All MPZS are oriented along the trajectory of the image of celestial bodies, in addition, a control unit for a mechanical device for moving the base (BUMU), a control unit and information processing unit for the main photodetector device (BUOFPU), a control unit for information processing and FPU star sensors (BUZD) are installed on the spacecraft , Scanning Control System (CLC), Motion and Navigation Control System (VESS), Antenna-Feeder System, Providing Two-Way Radio Communication with NPPOI for Any Spacecraft Orientation During Sky Viewing sphere and including low-directional antennas (MNA) with a wide radiation pattern, highly directional antennas (OHA) installed on two-axis drives, and a drive control unit ONA, in addition, an additional ground-based information receiving and processing point (PPOI) has been introduced into the space system ) and the Information and Analytical Center (IAC), and the composition of the NPPOI includes a computer complex for processing information and a system for controlling the means of the system, while the input to the optical system of the telescope receives from stars and other celestial objects, some of which are projected in the focal plane of the telescope onto the main FPU, and the other part onto the FPUZD, the OFPU output is connected to the input of the BUOFPU, the output of the FPUZD is connected to the input of the BUZD, the outputs of the BUOFPU are connected to the inputs of the transmitter and the main FPU , the outputs of the BUZD are connected to the inputs of the FPUZD, BUMU, SUDN and BUOFPU, the output of the BUMU is connected to the input of the MUPO, the outputs of the KUSU are connected to the inputs of the SUDN and the control unit for ON drives, the output of which is connected to the ON drives, the transmitter output is connected to ON, providing continuous radio communication with NPPOI and PPOI, the outputs of NPPOI are connected to the inputs of PPOI, IAC and system users, the output of IAC is connected to the input of NPPOI, the output of PPOI is connected to the input of NPPOI, in addition, the control complex, which is part of NPPOI, produces a program for viewing the celestial sphere, which is transmitted over the radio channel to the MNA of the spacecraft, the output of the MNA is connected to the input of the receiver, the output of which is connected to the input of the control panel, and the output of the subscriber of the system is connected to the input of the NCPAA, while the images of the starry sky obtained as a result of scanning are converted into digital the first form and are transferred to NPPOI where their final processing takes place. 17. The space system according to clause 16, characterized in that on board the spacecraft, which has one telescope in the observation equipment, a primary processing unit for the obtained images of the celestial sphere is introduced into the BUOFPU, during which celestial objects are detected, information about which is transmitted to ground items for further processing. 18. The space system according to clause 16, characterized in that two or more telescopes are introduced into the composition of the observation equipment on the SC, the field of view of which is separated in the direction perpendicular to the scanning direction, and form a single field of view of the observation equipment, the central axis of which is the axis of scanning . 19. The space system according to claim 17, characterized in that two or more telescopes are introduced into the composition of the observation equipment on the spacecraft, the field of view of which is separated in the direction perpendicular to the scanning direction, and form a single field of view of the observation equipment, the central axis of which is the axis of scanning . 20. The space system according to clause 16, characterized in that it consists of two or more spacecraft located at different points of standing in a geostationary or geosynchronous orbit, located in the field of visibility with NPPOI and PPOI and associated with NPPOI constant two-way radio communication, and with POI radio transmission of information from the spacecraft. 21. The space system according to claim 17, characterized in that it consists of two or more spacecraft located at different points of standing in a geostationary or geosynchronous orbit, located in the field of visibility with NNPPOI and PPOI and associated with NNPPOI with constant two-way radio communication, and with POI radio transmission of information from the spacecraft. 22. The space system according to p. 18, characterized in that it consists of two or more spacecraft located at different points of standing in a geostationary or geosynchronous orbit, located in the field of visibility with NPPOI and PPOI and associated with NPPOI constant two-way radio communication, and with POI radio transmission of information from the spacecraft. 23. The space system according to claim 19, characterized in that it consists of two or more spacecraft located at different points of standing in a geostationary or geosynchronous orbit, located in the field of visibility with NNPPOI and PPOI and associated with NNPPOI with constant two-way radio communication, and with POI radio transmission of information from the spacecraft. 24. The space system according to any one of paragraphs. 16, 17, 18, 19, 20, 21, 22, 23, characterized in that it introduces additional NPPOI located in different places on the Earth's surface, each of which is connected by a permanent two-way radio communication channel with one or more spacecraft.

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