RU2775095C1 - Method for viewing the geostationary region for detecting and observing space debris from a spacecraft - Google Patents

Abstract

FIELD: space technology.

SUBSTANCE: invention relates to space technology and can be used in the creation of space facilities and geostationary survey systems to obtain detailed images of space debris objects (SD) located in geostationary orbit (GSO) or periodically approaching it. The survey is performed from a spacecraft operating in autonomous or controlled mode from a flight control center. In autonomous mode, the spacecraft moves along the GSO below or above the GSO in an orbit, the parameters of which are calculated depending on the characteristics of the equipment that determine the maximum range for obtaining detailed images of the object. In autonomous mode, the object detection equipment is guided to the area of space located in front of the spacecraft around the geostationary orbit. This area is limited both in height, above and below the GSO, and to the north and south in a direction perpendicular to the equator plane. The size of this area is determined based on the analysis of the available catalogued man-made space objects in geostationary and geosynchronous orbits. After detecting the objects and determining their current coordinates and motion parameters, the equipment for obtaining detailed images is directed to the selected object, its detailed images are received and the received data are entered into the spacecraft memory block. The observation cycle is repeated. The information is transmitted over the radio line during communication sessions to the spacecraft flight control center. In the control mode of the spacecraft by commands from the flight control center, the object detection equipment is guided to the specified celestial coordinates, the object is detected and all operations are performed to determine its coordinates and motion parameters, which are transmitted to the control center. The flight control center, if necessary, transmits commands to maneuver the spacecraft to approach a given man-made object and obtain its detailed images.

EFFECT: dimensions of the area of outer space to be observed are determined; coordinates and motion parameters of detected objects are determined, their detailed images are obtained.

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Description

Geostationary orbit (GSO) is of particular importance for the placement of spacecraft for various purposes. Spacecraft (SC) in this orbit are constantly above the given areas on the earth's surface. This feature of the GSO is extremely important for communication, surveillance and control systems. However, it is impossible to place such a number of spacecraft on the GSO that satisfies international needs, so geosynchronous orbits have become widely used, having the same period of revolution, but differing from the GSO in eccentricity and inclination. Outer space near the GSO, in which these orbits are located, forms the geostationary region (GO) considered below.

The overload of the GEO with spacecraft and their exhausted stages of their launch, which turned into space debris, set the task of assessing their working condition for the possible organization of the removal of faulty and obsolete products from the GSO.

Since in most cases it is impossible to make such an assessment from the Earth's surface, it becomes necessary to create a specialized spacecraft to survey the geostationary region surrounding the GSO. To organize the work of such a spacecraft, it is necessary to determine the size and configuration of the area to be examined, select the parameters of the spacecraft's orbit, and set the objectives of its observations.

The purpose of the present invention is to determine the area of outer space to be observed, and to develop a method for detecting and observing space debris (SD) objects located in a selected area of the geostationary area from a spacecraft, determining their coordinates and motion parameters, as well as obtaining their detailed images.

Space systems are known that implement methods for surveying a geostationary region for detecting and observing objects located in this region.

The spacecraft of the SBSS system (Space-Based Space Surveillance Satellite) [1] was launched on September 26, 2010 into a low circular sun-synchronous orbit with an inclination of 97.97°, a perigee altitude of 625.0 km, an apogee altitude of 640.0 km, and an orbital period 97.42 min. The main payload is a visible sensor with a 30 cm telescope. The telescope is mounted on a two-axis gimbal with a high-speed drive, which gives it a wide field of view - three-quarters of the entire sky. The SBSS spacecraft operates 24 hours a day and can track every object in the geosynchronous orbit at least once a day.

The disadvantage of the SBSS spacecraft survey method is the impossibility of obtaining detailed images of observed objects in the geostationary region due to large distances to these objects.

JSC NPO Lavochkin proposed a method for surveying the geostationary orbit [2], implemented by spacecraft that are placed in semi-diurnal highly elliptical orbits (HEO) with an inclination of about 63.4° and a latitude argument in the region of 0° or 180°. Survey observation and measurement of the coordinates of the observed objects is carried out from two spacecraft with specialized optical equipment in a six-hour working segment of the orbit, which each spacecraft passes with a shift of 6 hours. For two turns, that is, within a day, a complete survey of the GEO can be provided with an observation range ranging from 17,000 to 18,000 km.

Obtaining detailed images of observed objects is proposed to be performed from two other spacecraft with different optical equipment when observing objects at a distance of 100 km to 400 km with a HEO having an apogee in the close vicinity of the GSO.

The disadvantage of this method of surveying the GSO is the need to use two pairs of spacecraft of different types with different optical observation equipment, placed on a HEO with different parameters.

The RF patent No. 2659379 [3] describes a method for surveying the geostationary region from a spacecraft moving along the HEO with an apogee in the altitude range from 200 km above to 500 km below the GSO and a perigee height of up to 5000 km, with an inclination from 0° to 5° . The observation range is determined by the characteristics of the onboard observation equipment. A method for the rational choice of HEO parameters is proposed, which provides obtaining detailed images of objects on the GSO in a minimum number of days. Obtaining detailed images is carried out in the controlled areas of the GSO from the working section of the HEO, which is symmetrical with respect to its apogee.

The disadvantage of this method is the impossibility of detecting an object in advance with a spacecraft and obtaining its detailed images.

As a prototype, a method for detecting and controlling space debris near a geostationary orbit, set forth in RF patent No. 2684253 [4], was adopted. The spacecraft of the described system is placed below the GSO at distances from 5280 km to 21894 km. It provides an overview of the entire GSO over a period of 4.5 to 0.5 days, respectively. The optical system of the spacecraft is placed on a turntable and directed upward towards the GSO. The GSO swath is formed by turning the field of view of the optical system around the spacecraft's orbital velocity vector into several discrete positions.

The disadvantage of the prototype should include the impossibility to preliminarily select the desired object at long distances, determine its coordinates and motion parameters, approach it and obtain its detailed images.

The technical result of the invention is to determine the configuration and size of the area of outer space to be observed to detect objects. This region is located around the geostationary orbit. It is limited both in height, by distances above and below the GSO, and by distances to the north and south in a direction perpendicular to the plane of the equator. The dimensions of this geostationary region are determined based on the analysis of the orbits of most geostationary and geosynchronous spacecraft in use.

The technical result of the invention consists in the choice of the spacecraft orbit, the parameters of which are assigned depending on the characteristics of the optical-electronic equipment for obtaining detailed images of objects placed on the spacecraft. These characteristics determine the maximum range allowed for obtaining images of the observed object with a given resolution when the spacecraft moves along a selected orbit above or below the GSO, or along an orbit specified by commands from the ground control station.

The technical result also consists in a method for detecting objects in the geostationary area, determining the coordinates and motion parameters of the detected objects and obtaining detailed images of the observed object.

These technical results are achieved by placing the spacecraft near the geostationary orbit, equipping it with an angular stabilization and orientation system, a power supply system, a thermal control system, data transmission and reception equipment capable of communicating with the spacecraft's ground flight control station. At the same time, the dimensions of the observation area of the geostationary region are selected based on the results of the analysis of the cataloged man-made space objects (TSO) located in the GO. In addition, the shape of the GO observation area is set in the form of a ring of rectangular cross section of the geostationary area (GSGO), located along the geostationary orbit (GSO), in which most of the cataloged TSO orbits are located completely from apogee to perigee. At the same time, the boundary of PSGO above the GSO is set to no more than 200 km, determined by the altitude of the disposal orbits of spacecraft that have completed their life cycle, the boundary below the GSO is set by the perigee height of most of the cataloged MSW, and to the south and north of the GSO by the inclination angle i of most of the cataloged MSW located in geosynchronous orbits. Moreover, the spacecraft is equipped with equipment for detecting MSW objects, determining their angular coordinates and motion parameters, equipment for obtaining detailed images of MSW objects, and a computer complex with a memory unit. In this case, the spacecraft is placed in a circular orbit in the plane of the equator or above the GSO for westward movement, or below the GSO for eastward movement. Moreover, equipment for detecting MSW objects, determining their angular coordinates and motion parameters, as well as equipment for obtaining detailed images of MSW objects are used in sequence to collect information about space debris and other objects. In addition, the height of the SC orbit is set from the GSO at a distance h km, determined from the conditions for the possibility of obtaining detailed images by the equipment of the largest number of MSW, according to the available cataloged data, located in the sphere of the space around the SC, the radius of the maximum range _Rpd for obtaining detailed images and at the same time ensuring the maximum possible drift velocity of the spacecraft (ω _dr ) relative to the GSO. The field of view of the equipment for detecting MSW objects, determining their coordinates and motion parameters in the direction of movement of the spacecraft drifting along the geostationary orbit to the area in which the PSGO moving parallel to the spacecraft is located is set. Moreover, the distance (D) from the spacecraft to the PSGO, at which the field of view of the equipment for detecting, determining the coordinates and parameters of the movement of objects of MSW completely covers the PSSO, is determined as a value calculated by the formula D=d/tg (ω _pz 12), where d is half diagonals of a rectangular PSGO, ω _pz - field of view of the spacecraft detection equipment. Next, calculate the angle of inclination θ of the field of view of the SC detection equipment down from the SC velocity vector according to the formula θ=arc sin D / 2R _GSO , where the GSO radius R GSO is equal to ₄₂₁₆₄ km, and direct the detection equipment to the selected PSGO.

Produce an overview of PSGO, detect, select from the stars the desired objects of TCR. The parameters of their movement are determined, compared with the available data in the memory block of the SC computing complex, and selected from the detected MSW objects to obtain their detailed images. The time of approach to them is calculated, at the estimated time the equipment for obtaining detailed images of objects is pointed at the selected MSW object. Its detailed images are obtained, the obtained data are entered into the memory block of the KA computer complex. Then, the review of the cross section of the geostationary area is resumed, and during communication sessions, the received information is transmitted via radio link to the spacecraft flight control point.

There is a variant in which the GO observation area is specified as part of the GO ring.

There is a variant in which, upon completion of the observation of a part of the PSGO ring, when the spacecraft is located in orbit above or below the GSO, the spacecraft is transferred to the orbit below or above the GSO, respectively, the detection equipment is pointed at the selected PSGO, the PSGO is surveyed, the desired TSO objects are detected, selected from the stars , determine the parameters of their movement, compare with the available data in the memory block of the SC computing complex, select from the detected TCR objects to obtain their detailed images, calculate the time of approach to them, point the equipment for obtaining detailed images of objects at the selected TCR object at the estimated time, receive it detailed images, the received data are entered into the memory block of the SC computer complex, then the review of the cross section of the geostationary area is resumed, and during communication sessions, the received information is transmitted over the radio link to the SC flight control point, and the SC maneuver up and down is repeated until a new command is received from the control point spacecraft flight.

There is a variant in which, in the control mode from the spacecraft from the spacecraft flight control point, the detection equipment is pointed at the celestial coordinates transmitted to the spacecraft from the spacecraft flight control point, survey is made in the given coordinates, the MSW object is detected, its coordinates and motion parameters are determined, and the data obtained transmitted via radio link to the spacecraft flight control point.

There is a variant in which, according to the commands transmitted from the spacecraft flight control point, the spacecraft flight orbit is changed, they switch to the rendezvous mode with a given object, when the required distance is reached, the equipment for obtaining detailed images is pointed at a given object and the resulting images are transmitted via radio link to the flight control point KA.

For the most part, space debris objects, which include failed spacecraft that have not yet been transferred to burial orbits, parts of rockets, etc., are distributed over heights in the same way as the above-mentioned spacecraft, and will also be observed in the geostationary space defined above. areas. Therefore, in the future, the observed set of operating spacecraft and these large elements of space debris will be denoted by the term "technogenic space objects" (MSO).

The proposed method for surveying the geostationary area is illustrated by the drawings in FIG. 1 - fig. 12.

Fig. 1 - shows the percentage of the number of spacecraft depending on the distance ±h [km] from the GSO.

Fig. 2 - a part of the geostationary region is shown, in which the entire orbits of 79% of the spacecraft and other large objects are located, the apogees and perigees of which are located in the altitude range of 200 km above the GSO and 200 km below the GSO and ± 200 km north and south of the equatorial plane at a height GSO, and their inclinations do not exceed 0.27°.

Fig. 3 - a part of the geostationary region is shown, in which the entire orbits of 80% of the spacecraft and other large objects are located, the apogees and perigees of which are located in the altitude range of 200 km above the GSO and 300 km below the GSO and ± 300 km north and south of the equatorial plane at a height GSO, and their inclinations do not exceed 0.4°.

Fig. 4, fig. 5 shows the observation schemes for obtaining detailed images of SO from a spacecraft moving in an orbit lying in the plane of the equator below the GSO.

Fig. 6 - the diagram of GO observation is shown, when the SC moves below the GSO to the east.

Fig. 7 - the diagram of GO observation is shown, when the spacecraft above the GSO moves to the west.

Fig. 8, 9, 10 - as examples, three options for the dimensions of the GO cross section are shown.

Fig. 11 - shows the diameter of the circle d, which completely includes PSGO,

where ω _pz - the angle of the field of view of the onboard detection equipment;

D is the distance from the spacecraft to the observed PS GO.

Fig. 12 shows the dependence of the size of the angles of the field of view of the detection equipment on the distances from the spacecraft to the observed cross sections.

The proposed method is implemented as follows. The spacecraft is placed near the geostationary orbit, equipped with an angular stabilization and attitude control system, a power supply system, a thermal control system, data transmission and reception equipment capable of communicating with the spacecraft ground control station. A spacecraft whose task is to survey the geostationary area, equipped with equipment for detecting space objects, equipment for obtaining their detailed images, a computer complex with a memory unit and receiving and transmitting equipment for a communication line with a flight control command post, must operate in two modes:

- offline mode, in which the spacecraft operates according to the programs embedded in its onboard computer system;

- the mode of observation of outer space and space objects by commands transmitted from the command post.

At the same time, the dimensions of the observation area of the geostationary region are selected based on the results of the analysis of the cataloged man-made space objects located in the civil defense. In addition, the shape of the GO observation area is set in the form of a ring of rectangular cross section of the geostationary area, located along the geostationary orbit, in which most of the cataloged TSO orbits are located completely from apogee to perigee. At the same time, the boundary of PSGO above the GSO is set to no more than 200 km, determined by the altitude of the disposal orbits of spacecraft that have completed their life cycle, the boundary below the GSO is set by the perigee height of most of the cataloged MSW, and to the south and north of the GSO by the inclination angle i of most of the cataloged MSW located in geosynchronous orbits. Moreover, the spacecraft is equipped with equipment for detecting MSW objects, determining their angular coordinates and motion parameters, equipment for obtaining detailed images of MSW objects, and a computer complex with a memory unit.

The proposed method for surveying the geostationary area includes determining the configuration and dimensions of the geostationary area in which the search, detection and acquisition of detailed images of TCR will be performed.

An analysis of the data given in the US A catalogs (UCS Satellite Database) [5] and the ESOS report [6] Classification of geosynchronous objects for 2018, from January 2016 to January 2021, showed that the number of active spacecraft in the geosynchronous orbit region is constant increases: 2016 - 493 SC, 2018 - 519 SC, 2019 - 551 SC, 2021 - 562 SC.

The ESOS report shows that there were 1526 large objects in the GEO area in 2018. The distribution of spacecraft by altitude over the years has practically not changed. It can be assumed that this trend will continue in subsequent years.

According to the NAS A catalog for March 2019, 80% of geostationary and geosynchronous spacecraft have orbits whose apogees are located in the altitude range from 0 to 25 km above the GSO (35786 km is the height of the GSO above the Earth's surface at the equator), and their perigees are in the range altitudes from 0 to 25 km below GSO. When considering the altitude range from 0 to 50 km, the number of spacecraft whose apogees and perigees of orbits are located in this range, respectively, above and below the GEO, increases to 86%. With further expansion of the altitude range from 0 to 100 km above and below the GEO, the number of spacecraft increases to 93%, respectively, and in the altitude range from 0 to 200 km above and below the GSO, the number of spacecraft increases to 96%. The percentage of the number of spacecraft depending on the distance ±h [km] from the GSO is shown in FIG. one.

Orbital inclinations K A are distributed as follows. About 77% of spacecraft have an inclination from 0° to 0.14°, which corresponds to a deviation of ~100 km from the equatorial plane at the GSO height. In the inclination range from 0° to 0.27° (deviation up to ~200 km from the equatorial plane), about 79% of spacecraft and about 80% of spacecraft, of all those listed in the catalog, have an inclination from 0° to 0.4° (deviation up to ~300 km from the equatorial plane). The remaining K A have an inclination greater than 0.4°.

Therefore, if we restrict the observable region of outer space near the GSO to a ring with a cross section of the geostationary region ring with dimensions of 100 km above the GSO, 100 km below the GSO, and ±100 km north and south of the equatorial plane at the height of the GSO, then in this region there will be completely orbits 77% of spacecraft and other large objects, the apogees and perigees of which are located in this range of heights, and their inclinations do not exceed 0.14°.

If we limit the observed region of outer space by a ring with PSGO with dimensions of 200 km above the GEO (above 200 km is the disposal area for failed geostationary spacecraft), 200 km below the GEO and ± 200 km north and south of the equatorial plane at the height of the GSO, then in this the regions will be located completely in the orbits of 79% of the spacecraft and other large objects, the apogees and perigees of which are located in this altitude range, and their inclinations do not exceed 0.27°. Part of this geostationary region is shown schematically in FIG. 2.

If we limit the observed region of outer space to a ring with PSGO with dimensions of 200 km above the GSO, 300 km below the GSO, and ±300 km north and south of the equatorial plane at the height of the GSO, then the total number of spacecraft and other large objects whose apogees and perigees are located in this altitude range, and their inclination does not exceed 0.4°, will increase to 80%. Part of this geostationary region is shown schematically in FIG. 3.

The specified dimensions of the observed GO can be changed depending on the tasks set for observing objects and the capabilities of the optoelectronic onboard surveillance equipment.

Objects whose apogee, perigee, and orbital inclination exceed the selected PSGO values will cross the annular region of outer space with the indicated cross sections twice a day and, therefore, will be available for detection and observation in this region in part of their orbits.

To implement the proposed method, the spacecraft is placed in a circular orbit in the equatorial plane or above the GSO for westward movement, or below the GSO for eastward movement. Moreover, equipment for detecting MSW objects, determining their angular coordinates and motion parameters, as well as equipment for obtaining detailed images of MSW objects are used in sequence to collect information about space debris and other objects. In addition, the height of the spacecraft orbit is set from the GSO at a distance h km, determined from the conditions for the possibility of obtaining detailed images by the equipment of the largest number of MSW, according to the available cataloged data, located in the sphere of space around the spacecraft with a radius of the maximum range _Rpd of obtaining detailed images and at the same time ensuring the maximum possible spacecraft drift velocity (ω _dr ) relative to GSO.

The proposed method for surveying the GSO during the operation of the spacecraft in autonomous mode includes the choice of the orbit of the spacecraft for the survey of the geostationary region described above.

Detection, determination of the coordinates and parameters of the movement of MSW, as well as obtaining their detailed images in the geostationary region from a spacecraft requires the fulfillment of several conflicting requirements:

- detection, determination of coordinates and motion parameters of the largest number of objects in the minimum time;

- obtaining detailed images with a given resolution of selected (given) objects to assess their state at a given time;

- ensuring the minimum consumption of the characteristic velocity in the performance of these tasks to extend the time of the spacecraft.

The requirement for the minimum characteristic velocity consumption is met when the spacecraft is placed in a circular orbit in the equatorial plane (or at a slight angle to it) above or below the GEO height at such a constant distance h from the GEO that makes it possible to obtain detailed images of the largest number of objects located in the above-described geostationary area.

The spacecraft can obtain detailed images of objects within the sphere of outer space, described around it with a radius equal to the maximum range for obtaining detailed images of the onboard observation equipment. Installed in a circular orbit in the equatorial plane or with its slight inclination with a radius slightly less than or greater than the radius of the GEO, the spacecraft will be able to obtain detailed images of all objects crossing this sphere while drifting relative to the GEO.

For the example in FIG. 4, fig. 5 shows the observation schemes for obtaining detailed images of SSR from a spacecraft moving in an orbit lying in the plane of the equator below the GEO. Since the size of the limiting range for obtaining detailed images is small compared to the radii of orbits close to the GSO, in Fig. 4, fig. 5 shows the portions of these orbits to be observed as straight parallel lines. A circle drawn with radius L with a KA located in an orbit separated from the GSO at a distance h [km] shows the space where it is possible to obtain detailed images of the observed objects. L is the maximum range for obtaining detailed images of objects observed from the spacecraft.

When choosing a spacecraft orbit, it should be taken into account that when installing a spacecraft to obtain detailed images of objects at a close distance from the GSO, the spacecraft drift velocity will be small, and, in addition, due to the large number of objects in this area, there is a high probability of a spacecraft collision with them.

Calculations have shown that in the range of distances from the GSO ±(0 - 300) km, the drift velocity of the spacecraft _ωdr depends on the distance h almost linearly. Therefore, we can approximately take:

ω _dr \u003d 0.013 h [degree / day] when the spacecraft drifts below and above the GSO.

At distances from the GSO h=10 km, the spacecraft drift velocity is 0.13 degrees/day. An increase in the drift velocity, i.e., a decrease in the survey time of the entire GEO or its specified part, while maintaining the possibility of obtaining detailed images, requires the installation of a spacecraft at a greater distance from the GEO and the use of observation equipment with an appropriate range for obtaining detailed images.

To obtain images of 80% of objects in any part of their orbits, it is necessary to have equipment for obtaining detailed images with a range L of at least 50 km and install KA at a distance of 25 km above or below the GEO. In this case, the spacecraft drift relative to the GSO will be 0.32 degrees/day, and the total number of observed objects for obtaining their detailed images will reach 92% (Fig. 4).

For a drift rate of 1°/day, the spacecraft must be put into a circular orbit at a distance h=77.5 km above or below the GEO. At the same time, equipment capable of obtaining detailed images of objects at a distance of L=100 km will make it possible to obtain images of 96% of objects (Fig. 5).

Thus, depending on the characteristics of the observation equipment that determine the range L for obtaining detailed images of objects, such a distance h of the spacecraft from the GSO is chosen (that is, the radius of its circular orbit lying in the equatorial plane is determined), which satisfies the requirements for observing the geostationary region both in terms of speed drift of the spacecraft relative to the GEO (the survey time of the entire GSO or a given part of it), and by the number of observed objects.

All considerations regarding the choice of the spacecraft orbit referred to the case when the orbits of the observed objects are in the plane of the geostationary orbit, that is, in the plane of the equator, or had a slight inclination. If it is necessary to observe objects located in orbits with a significant inclination, it must be taken into account that obtaining detailed images of such objects is possible only in the vicinity of the ascending and descending nodes of their orbits, when the shortest distance from the current position of the object to the GSO does not exceed the limiting range for obtaining images with the required quality. The duration of the presence of objects in such parts of the orbit is limited and depends on the inclination of the orbit: the greater the inclination of the orbit, the shorter the duration of the object's stay in the region of favorable conditions for its observation.

Having established the spacecraft orbit, we will determine the conditions for detecting and determining the motion parameters of objects located in the GO.

To obtain detailed images of an object, it is necessary to detect the object ahead of the SC moving relative to the GSO, determine the parameters of the object’s movement, the distance from the SC to the object, and, knowing the SC drift velocity, calculate the time and conditions for approaching the object.

Observation of PSGO, both in front of and behind a spacecraft placed in orbit near the GEO, makes it possible to observe all objects whose orbits are in the perspective of the observed sections, at any point of their orbits from perigee to apogee for a long time (up to several days) and choose the time of observation at the best angles of illumination of objects by the Sun. Objects with orbits whose dimensions and inclinations exceed the selected PSGO values will cross this region and during this time will be observed twice a day in the middle parts of their orbits.

To implement the proposed method, the field of view of the equipment for detecting MSW objects, determining their coordinates and motion parameters in the direction of motion of the spacecraft drifting along the geostationary orbit, to the area in which the PSGO moving parallel to the spacecraft is located, is set. Moreover, the distance (D) from the spacecraft to the PSGO, at which the field of view of the equipment for detecting, determining the coordinates and parameters of the movement of objects of MSW completely covers the PSSO, is determined as a value calculated by the formula D=d/tg (ω _pz /2), where d is half diagonals of a rectangular PSGO, ω _pz - field of view of the spacecraft detection equipment. Next, calculate the angle of inclination θ of the field of view of the SC detection equipment down from the SC velocity vector according to the formula θ=arc sin D / 2R _GSO , where the GSO radius R GSO is equal to ₄₂₁₆₄ km, and direct the detection equipment to the selected PSGO.

Detection of GO objects with the selected PSGO is carried out by pointing the field of view of the object detection equipment at the PSGO in front of the moving relative GSO of the spacecraft.

In order for numerous objects located in the geostationary region from the spacecraft to the region where the detected objects are located not to fall into the field of view of the observation equipment, it is necessary that the top of the field of view to the observed region be lower than the region of space in which most of the objects are located. The boundary of this area, as shown by the analysis of the catalogs, is located above 25 km and 25 km below the GSO.

In FIG. 6 shows the GO observation scheme when the spacecraft moves eastward below the GSO, and Fig. 7 - scheme of observation of the motion of the spacecraft above the GSO to the west.

The diagrams show the following symbols:

VG - the upper boundary of the ring GO;

NG - the lower boundary of the ring GO;

AB - cross section of GO;

op. SC - SC orbit;

ω _pz1 , ω _pz2 - angles of the field of view of the equipment for detecting objects;

θ ₁ , θ2 - angles of inclination of the field of view of the observation equipment from the velocity vector of the spacecraft;

CF - distances from the spacecraft to the observed cross section of the GO;

e ₁ g ₁ and e ₂ g ₂ - segments of longitudes on the GSO, observed from the spacecraft;

λ ₁ , λ ₂ - geocentric angles covering the sections of longitudes in GO, observed from the spacecraft;

λ ₃ , λ ₄ - geocentric angles covering longitudes on the GSO, observed from the spacecraft.

In FIG. 8, 9, 10 as examples, three options for the dimensions of the GO cross section are shown.

Fig. 8: (+100) km above and (-100) km below the GSO in the plane of the equator;

±100 km north and south of the equatorial plane.

In this cross section of the GO there are 92% of the spacecraft, in which the semi-major axis of the orbits is located within these limits, and 77% of the spacecraft with inclinations of no more than 0.14°.

Fig. 9: (+200) km above and (-200) km below GSO in the plane of the equator;

±200 km north and south of the equatorial plane.

In this cross section of the GO there are 95% of the spacecraft, in which the semi-major axis of the orbits is located within these limits, and 79% of the spacecraft with inclinations of no more than 0.27°.

Fig. 10: (+200) km above and (-300) km below the GSO in the plane of the equator;

±300 km north and south of the equatorial plane.

This GO cross section contains 97% of spacecraft whose apogees and perigees are located within these limits, and 80% of spacecraft with inclinations of no more than 0.4°.

The distance from the spacecraft to the PSGO is determined depending on the size of the field of view of the spacecraft detection equipment (PZAO), into which the entire cross section of the GO fits completely. Let us assume that the receiving square array is completely inscribed in the field of view of the telescope.

In FIG. eleven:

d is the diameter of the circle, which completely includes PSGO;

ω_pz - field of view angle of onboard detection equipment;

D is the distance from the spacecraft to the observed PS GO.

It follows from the figure: D=d/2tg(ω _pz /2).

For options (a), (b), (c) the calculated distances D at ω _pz =1°; 2°; 3°; 4°; 5°; 6° are given in the table:

The distances from the spacecraft to the observed cross sections, depending on their sizes and the angles of the field of view of the detection equipment, are shown in the graphs of Fig. 12.

Having determined the distance D to the observed PSGO, the angle of inclination of the field of view of the detection equipment from the velocity vector of the spacecraft is calculated to point the field of view of the detection equipment at the PSGO.

It is known from geometry that the value of the angle formed by the tangent and the chord passing through the point of contact is equal to half the value of the arc fixed between its sides. In this case, the chord is the calculated distance D. Thus, the angle of inclination θ of the field of view of the detection equipment down from the spacecraft velocity vector is determined by the formula θ=arc sin D / 2R _gso , where the GSO radius R _gso =42164 km.

Having data on the size of the field of view of the detection equipment ω _pz and the angle of inclination of the field of view θ from the velocity vector of the spacecraft, the detection equipment is pointed at the PSGO located at the calculated distance D from the spacecraft.

A spacecraft installed in a circular orbit below or above the GEO, which differs from the GSO by h km, drifts along the GEO at a speed ω _dr = 0.013⋅h [degree/day] and makes a regular survey of the GO cross section moving with it at a distance D. The detected objects are selected from interference according to the criteria laid down in the computer complex, the objects are selected to obtain their detailed images, the time to approach them is calculated, at the calculated time, the equipment for obtaining detailed images is pointed at them one by one. After obtaining detailed images, the received information is entered into the memory block and the review of the GO cross section is resumed.

In the autonomous mode of operation, the spacecraft during communication sessions with the control center transmits all the information received and receives new data to replenish the catalog of objects in the onboard computer.

In the spacecraft control mode by commands from the control center, optoelectronic detection equipment is directed to a given point in outer space, detects an object and performs all operations to determine its coordinates and motion parameters, which are transmitted to the control center. In addition, the control point, if necessary, transmits commands to perform a spacecraft maneuver to approach a given object and obtain its detailed images. Sources of information.

1. Cherny I. A satellite for monitoring the space situation was launched. News of cosmonautics. No. 11. 2010. P.34-36.

2. Klimenko N.N., Nazarov A.E. A promising space system for observing the geostationary orbit. "Bulletin" NPO im. S.A. Lavochkin. No. 4. 2015. P.16-22.

3. Patent of the Russian Federation No. 2659379 "Method of surveying the geostationary region for observing elements of space debris and other objects from a spacecraft in a semi-diurnal highly elliptical orbit."

4. Patent of the Russian Federation No. 2684253 "Method for detecting and monitoring space debris near the geostationary orbit."

5. http://www.ucsusa.org/nuclear-weapons/space-weapons/satellite-database

6. Classification of geosynchronous objects ESOS 08.2018.

Claims (4)

1. A method for surveying a geostationary area for detecting and observing space debris from a spacecraft, in which the spacecraft is placed near a geostationary orbit, equipped with an angular stabilization and orientation system, a power supply system, a thermal control system, data transmission and reception equipment, configured to communicate with a ground control station for the flight of a spacecraft (SC), characterized in that the dimensions of the observation area of the geostationary area (GO) are selected based on the results of the analysis of cataloged man-made space objects (TSO) located in the GO, while the shape of the GO observation area is set in the form of a ring or part ring of rectangular cross section of the geostationary region (GSGO), located along the geostationary orbit (GSO), in which most of the cataloged TSO orbits are located completely from apogee to perigee, in addition, set the GSO boundary above the GSO no more than 200 km, determined by the altitude the boundary below the GSO with the perigee height of most of the cataloged MSW, and to the south and north of the GSO by the inclination angle i of the majority of the cataloged MSW located in geosynchronous orbits, while the spacecraft is equipped with equipment for detecting MSW objects, determining their angular coordinates and motion parameters, equipment for obtaining detailed images of MSW objects, a computer complex with a memory unit, and the spacecraft is placed in a circular orbit in the equatorial plane or above the GSO for westward movement, or below the GSO for eastward movement, and the object detection equipment is used sequentially SCR, determination of their angular coordinates and motion parameters, as well as equipment for obtaining detailed images of SCR objects for collecting information about space debris objects, in addition, the height of the SC orbit is set from the GSO at a distance h km, determined from the conditions for the possibility of obtaining detailed and images of the largest, according to the available cataloged data, the amount of MSW located in the sphere of space around the spacecraft with a radius of maximum range R _d for obtaining detailed images, and at the same time ensuring the maximum possible drift speed of the spacecraft (ω _dr ) relative to the GSO, establish the field of view of the MSW object detection equipment, determining their coordinates and motion parameters in the direction of motion of the spacecraft drifting along the geostationary orbit to the area in which the PSGO moving parallel to the spacecraft is located, and the distance (D) from the spacecraft to the PSGO, at which the field of view of the equipment for detecting, determining the coordinates and parameters of movement of objects TKO completely covers PGSO, is defined as a value calculated by the formula D=d/tg (ω _pz /2), where d is half of the diagonal of a rectangular PSGO, ω _pz is the field of view of the SC detection equipment, calculate the angle of inclination θ of the field of view of the SC detection equipment down from the spacecraft velocity vector according to the formula θ=arc sin _D /2R _GSO c is equal _to 42164 km, and point the detection equipment at the selected PSGO, survey the PSGO, detect, select the desired TSR objects from the stars, determine the parameters of their movement, compare with the available data in the memory block of the SC computing complex, select from the detected TSR objects to obtain them detailed images, calculate the time of approach to them, at the estimated time point the equipment for obtaining detailed images of objects at the selected TCR object, obtain its detailed images, enter the obtained data into the memory block of the SC computer complex, then resume the review of the cross section of the geostationary area, and during communication sessions the received information is transmitted via a radio link to the spacecraft flight control point. 2. The method of surveying the geostationary region according to claim 1, characterized in that upon completion of the observation of a part of the PSGO ring, when the spacecraft is located in orbit above or below the GSO, the spacecraft is transferred to an orbit below or above the GSO, respectively, the detection equipment is pointed at the selected PSGO, a review is made PSGO, detect, select the desired SSR objects from the stars, determine the parameters of their movement, compare with the available data in the memory block of the SC computing complex, select SSR objects from the detected objects to obtain their detailed images, calculate the time of approach to them, at the estimated time direct the acquisition equipment detailed images of objects on the selected TCR object, its detailed images are obtained, the obtained data are entered into the memory block of the SC computing complex, then the review of the cross section of the geostationary area is resumed, and during communication sessions, the received information is transmitted over the radio link to the SC flight control point, and the SC maneuver is up -down repeat d about the arrival of a new command from the spacecraft flight control point. 3. The method of surveying the geostationary area according to claim 1, characterized in that in the control mode from the spacecraft from the spacecraft flight control point, the detection equipment is directed along the celestial coordinates transmitted to the spacecraft from the spacecraft flight control point, the survey is made in the given coordinates, the TKO object is detected , its coordinates and motion parameters are determined, and the received data are transmitted via radio link to the spacecraft flight control point. 4. The method of surveying the geostationary area according to claim 1, characterized in that, according to the commands transmitted from the flight control center of the spacecraft, they change the orbit of the spacecraft, switch to the rendezvous mode with a given object, after reaching the required distance, the equipment for obtaining detailed images is pointed at a given object and the received images are transmitted via radio link to the spacecraft flight control point.

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