RU79362U1 - CORPORATE SYSTEM FOR RECEIVING SPACE INFORMATION FOR THE DESIGN AND OPERATION OF EXTENDED ENGINEERING STRUCTURES, FOR EXPLORATION OF OIL AND GAS DEPOSITS AND THEIR EQUIPMENT AND OPERATION - Google Patents

Abstract

The corporate system for obtaining space information includes solar-synchronous satellites 1, 2 with multizone optical devices and hyperspectrometers on board, solar-synchronous satellites with synthesized aperture radars and a radio communication channel, devices for determining orbit parameters, as well as stationary and mobile receiving stations. Synthesized aperture radars are configured to transmit an interferometric signal, and communication channels are in the form of broadband radio channels. Stationary and mobile receiving stations 4, 5, 6 are connected to operators 7, consumers 8 of information and equipped with operational control modes for monitoring and dumping information, and devices for determining the orbit parameters are installed on satellites 1, 2. Of the two satellites moving in one or near orbits 1, 2 is formed by the tandem of satellites 1, 2 by synchronizing their radars in phase of the emitted signals with the possibility of obtaining radar images of the earth's surface simultaneously at different angles. Each of satellites 1, 2 is equipped with an on-board switching device, a time frequency system, an orientation and stabilization system controller, a navigation system controller, a synchronizer and a bi-directional code exchange controller. Moreover, the corporate system is equipped with at least one geostationary navigation satellite 3 with communication, relay and radio navigation devices connected to solar-synchronous satellites and to stationary and mobile stations 4, 5, 6. Radar with a synthesized aperture of the solar-synchronous satellite 1

Description

The utility model relates to systems for the comprehensive receipt, reception, processing, storage and dissemination of aerospace Earth monitoring data for exploration, monitoring the state of change dynamics and predicting changes in oil and gas industry objects and the environmental situation in the areas of these objects and ice emergencies.

All over the world, exploration of the Earth from space is becoming comprehensive. The most informative method for solving problems of remote exploration of the Earth's surface from space is the use and thematic analysis of images obtained by instrument complexes of different frequency ranges installed on spacecraft. A number of satellites equipped with remote sensing instruments (radars, radiometers and optical equipment) have been put into orbit specifically to obtain versatile geophysical information necessary for assessing the state of the environment and for environmental research.

Remote sensing materials are obtained as a result of non-contact shooting from aircraft, spacecraft, ships and submarines, and ground stations. The resulting documents are very diverse in scale, resolution, geometric, spectral and other properties. It all depends on the type and height of the survey, the equipment used, as well as on the natural features of the area, atmospheric conditions, etc.

Known space system for the implementation of information exchange (a system for obtaining space information), containing a gravitationally stabilized linear bunch of antenna elements (AE), made in the form of receivers / emitters with different radiation patterns, means of phase synchronization AE, combined with a control system and / or control for the relative motion of the AE, which is equipped with additional similar ligaments of AE located in a given neighborhood of the reference point of the cable

a system (TS) moving in a close to circular near-Earth orbit, and the phase synchronization means and said control and / or control system are respectively configured to carry out phase synchronization, control and / or control (RU No. 2169990).

A multifunctional telecommunication space system (space information acquisition system) is known, including a communication subsystem and a monitoring subsystem. The communication subsystem is built on the basis of satellite repeaters and provides telephone communications, video conferencing, image transmission, machine exchange, Internet access on a global scale with speeds from 1, 2 kbit / s to 2948 kbit / s. The operation of the satellite constellations is carried out using ground-based relays included in control stations located at the calculated points of the earth's surface at the intersection of the radio visibility zones of neighboring spacecraft. The space segment of the system includes three groups of spacecraft for the system of high and low speed communications and monitoring. The first two constellations include 24 satellites in orbits with an altitude of 10,360 km, and the monitoring constellation includes 8-12 spacecraft at an altitude of 600 km. The Earth segment of the system consists of 12-14 coordinating stations combined with the control stations of the monitoring subsystem and playing the role of regional stations, as well as a fleet of mobile and stationary subscriber stations. Service signals (call, request, answer, etc.) are transmitted through the nearest spacecraft via feeder lines to the coordinating station, which, having information about all the subscribers of the system and their coordinates, as well as data on the free channels of all spacecraft, makes route routes signals from one subscriber to another. The space monitoring system includes spacecraft for optical and radar surveillance. To conduct monitoring of the object, information about the need for monitoring is transmitted to the coordinating station in the area of which the required spacecraft is located, and after receiving monitoring information it is reset to the nearest control station and then to the user. The system requires a significant number of spacecraft (minimum 56), which makes it difficult to manage these satellites. Moreover, communication in the system is carried out through several spacecraft and ground stations, which increases the time

the passage of communication signals and / or monitoring and degrades their quality (RU No. 2169433).

A multifunctional space communication system is known ((a system for obtaining space information), including a constellation of satellites placed in a geostationary orbit, a constellation of satellites placed in a low altitude orbit, and at least one ground control point, characterized in that the system is equipped with a constellation of satellites placed in a medium altitude orbit moreover, at least one satellite located in a geostationary orbit is connected via a communication line to a ground control point, satellites, in geostationary orbit, are connected to each other by high-speed communication lines and are designed to relay control signals from a ground control point to satellites located in medium and low altitude orbits, with which they can connect via communication lines, and relay information signals received from satellites of medium and low altitude orbits to the ground control point, while each of the satellites located in low altitude orbit has the ability to communicate with at least one of the satellites located in the mid-altitude orbit, and each of the satellites located in this orbit with one of the satellites in the geostationary orbit (RU No. 2302695, prototype).

The disadvantages of the known systems are the relatively low efficiency of observation, in particular:

- the range of observed objects in brightness is limited by the dynamic range of photodetector circuits in the EIA;

- the flow of the information taken is limited by the bandwidth of a single radio channel;

- insufficient productivity (the amount of information transmitted) and efficiency;

the impossibility of transmitting information ready for use by the consumer, since the formation of the radar image should be carried out by the ground-based satellite information processing center and transmitted to the consumer after some time necessary for its preparation

and communication with the consumer. This imposes restrictions on many users located at remote locations.

The technical task of the utility model is to expand the arsenal of radar systems deployed on satellites, and to create a space radar that provides a detailed survey of the Earth’s surface with specified quality characteristics and delivers the finished radar image obtained in wide mode directly to any consumer in real time without presenting high requirements for the technique of receiving equipment, as well as having enhanced adaptive capabilities and survivability.

The technical result that provides the solution of the problem lies in the fact that a significant increase in the monitoring efficiency is provided due to a simultaneous increase in the flow of recorded information, an increase in productivity and efficiency, an increase in the reliability of the monitoring system due to an increase in the efficiency conservation coefficient and the operational readiness coefficient, and a decrease in the role of the human factor and corporate interests in the formation of objective information about the state of a potentially dangerous facility in extensive engineering structures in the interests of the objective adoption of effective management decisions both in everyday activities and in emergency situations, increasing the level of integration of existing industry (regional, corporate) monitoring systems in the interest of effectively using their information potential to solve public administration tasks, ensuring the level automation of information exchange, ensuring a high-quality solution of functional tasks by a system of automated of operational control of potentially dangerous objects - extended engineering structures, increased efficiency and rationality of aggregation and integration of existing monitoring systems for high-quality and safe solutions of functional tasks. At the same time, the maximum possible use of digital methods for generating and processing signals, the ability to change the program of work of the space radar during development and operation in orbit, the ability to control the beam of the antenna system in the vertical plane, the ability to expand the sector of the angle of incidence of the beam, and the ability to pair radar information

information from other sources, such as optical or infrared, placed on the spacecraft.

The essence of the utility model is that the corporate system for obtaining space information includes solar-synchronous satellites with multizone optical devices and spectrometers on board, solar-synchronous satellites with synthetic aperture radars and a radio channel, devices for determining orbit parameters, as well as stationary and mobile receiving stations, while spectrometers on board solar-synchronous satellites are made in the form of hyperspectrometers, synthetic aperture radars They are made with the possibility of transmitting an interferometric signal, and the communication channels are in the form of broadband radio channels with the possibility of transmitting an interferometric signal to stationary and mobile receiving stations, which are equipped with the means of operational control of the observation and data reset modes, and the orbit parameters determination devices are installed directly on solar-synchronous satellites.

Preferably, a tandem of satellites is formed from at least two solar-synchronous satellites with synthetic aperture radars by synchronizing their radars in phase of the emitted signals with the possibility of obtaining radar images of the earth's surface simultaneously at different angles.

Moreover, each of the solar-synchronous satellites is equipped with an on-board switching device, a time frequency system, an orientation and stabilization system controller, a navigation system controller, a synchronizer and a bi-directional code exchange controller.

Moreover, the corporate system is equipped with at least one geostationary satellite with communication, relay and radio navigation devices connected to solar-synchronous satellites and to stationary and mobile stations, and the radar with a synthesized aperture of the solar-synchronous satellite contains a phased monitoring unit antenna system, antenna radiation pattern control unit, radio transmitting and receiving devices, digital processing device, interface device and an information exchange unit. Block at the same time

monitoring mode control includes a central processor unit, an internal bus controller and an address-data controller for an on-board switching device, an on-board time frequency system controller, an orientation and stabilization system controller, a navigation system controller, a synchronizer and a bi-directional code exchange controller, and the antenna system is made with many sectional, for example, twelve sectional waveguide-slotted web.

In particular cases of implementation, stationary and mobile receiving stations include forecasting terminals for scientific data and design data, raw material production data, underground storage facilities, construction data, oil production data, oil and gas processing data, ice and environmental data.

Figure 1 shows a functional diagram of a corporate system for obtaining space information, figure 2 is a block diagram of a radar with a synthesized aperture of a solar-synchronous satellite; figure 3 is a block diagram of a receiving station.

The essence of the utility model is that the corporate system for obtaining space information includes solar-synchronous satellites 1, 2 with multizone optical devices and spectrometers on board, solar-synchronous satellites with synthesized aperture radars and a radio channel, devices for determining orbit parameters, and also stationary and mobile receiving stations, while spectrometers on board solar-synchronous satellites are made in the form of hyperspectrometers, radars with synthesized aperture Uroy are made with the possibility of transmitting an interferometric signal, and the communication channels are in the form of broadband radio channels with the possibility of transmitting an interferometric signal to stationary and mobile receiving stations 4, 5, 6, which are connected to operators 7, consumers 8 of information and equipped with operational control modes of observation and information dumping (not shown), and devices for determining the parameters of the orbit (not shown) are installed directly on the solar-synchronous satellites 1, 2.

Preferably, at least two solar-synchronous satellites 1, 2 moving in one or close orbits with a time interval, with synthetic aperture radars, are formed by a tandem of satellites 1, 2 by synchronizing their radars in phase with the emitted signals

the ability to obtain radar images of the earth's surface at different angles simultaneously. Moreover, each of the solar-synchronous satellites 1, 2 is equipped with a hyperspectrometer, an on-board switching device, a time frequency system, an orientation and stabilization system controller, a navigation system controller, a synchronizer and a bi-directional code exchange controller (not shown).

In this case, the corporate system is equipped with at least one geostationary navigation satellite 3 with communication, relay and radio navigation devices connected to solar-synchronous satellites and to stationary and mobile stations 4, 5, 6. As stations 4-6, they can be used centers of industrial monitoring systems, dispatch centers of departmental monitoring systems, central specialized archives of monitoring information of some Federal agencies, situational centers of the Government of the Russian Federation.

The synthesized aperture radar of the solar-synchronous satellite 1 and 2 comprises a monitoring mode control unit 7, a phased antenna system 8, a radiation pattern control unit 9 of the antenna system 8, a radio transmitting and receiving device 10, 11, respectively, a digital processing device 12, an interface device 13 and block 14 exchange of information. The monitoring mode control unit 7 includes a central processing unit (BCP) 15, an internal bus controller (KVSh) 16 and an address data (SHAD) connected to the bus 17 controller 18 on-board switching apparatus (KBKA), a controller 19 on-board time frequency system (UHF) , the controller 20 of the orientation and stabilization system (KSSO), the controller 21 of the navigation system (SPE), the synchronizer 22 and the controller 23 bidirectional code exchange (KCO). The antenna system 8 is made with a multi-sectional, for example, twelve sectional waveguide-slotted web.

In particular cases of implementation, stationary and mobile receiving stations include forecasting terminals for scientific data and design data, raw material production data, underground storage facilities, construction data, oil production data, oil and gas processing data, ice and environmental data.

Stations 4, 5, 6 of receiving signals from satellites 1, 2 consist of antenna systems 25, 26. terminal 27, high-speed radio line equipment 28, primary processing and registration unit 29, information generation unit 30, unit 31

computing the parameters of the orbit, the device 32 storage of information, the local network 33, block 34 analysis and evaluation of the quality of information and device 35 control and monitoring.

The corporate space information acquisition system works as follows.

Solar-synchronous satellite 1, 2 is an artificial Earth satellite located in a solar-synchronous orbit that monitors sections of its surface at the phase angles of the Sun that do not change for each of them. This means that the height of the Sun above the same parts of the surface, extending under satellite 1, 2, remains unchanged during the next passage of satellite 1, 2 above them. In other words, the local time of day of satellite 1, 2 flight over each part of the terrain remains unchanged (if seasonal changes in the height of the Sun are not taken into account). The orbit of a geostationary satellite 3 is called a circular orbit lying in the plane of the Earth's equator, having a radius at which the period of revolution of satellite 3 is equal to the period of rotation of the Earth around its axis. In this case, satellite 3 is constantly above the same point on the surface of the Earth. Satellite 3 provides navigation services for satellites 1,2 and stations 4-6, and also provides an uninterrupted exchange of information - remote sensing materials - between satellites 1, 2 and stations 4-6.

Remote sensing materials are obtained as a result of non-contact imaging by satellites 1, 2. Radio waves, almost not absorbed, freely pass through clouds and fog. Night darkness is also not an obstacle for shooting, it is conducted in any weather and at any time of the day. The main qualities of the obtained remote images are their high detail, the simultaneous coverage of vast spaces, the ability to obtain repeated images and study of inaccessible territories. Moreover, the images can be black-and-white zonal and panchromatic, color, color spectrozonal, and even - for better distinguishability of some objects - false color, i.e. made in conventional colors. The hyperspectrometer is characterized in that it provides a combination of spectral resolution with spatial resolution, which allows multidimensional coordinate-spectral measurements in spectral channels, the number of which

reaches 200, with a spatial resolution of 30-50 m in a capture band of 30-50 km. The orbital parameters are determined directly on satellites 1, 2.

A radar with a synthesized aperture of the solar-synchronous satellite 1 and 2, forming an image in real time, operates as follows. Block 7 provides the exchange with other airborne systems and general control of radar devices, the antenna system 8 generates a radiation pattern with controlled parameters and the ability to scan in the elevation plane, block 9 sets the desired state of the phase shifters of the antenna system 8, providing control of the radiation pattern, the device 10 provides the transfer of radio pulses on the carrier frequency and their amplification to the required level of radiation power, the device 11 provides a preliminary effort receiving the signal at the carrier frequency and transferring the spectrum to the first intermediate frequency, the device 12 will provide the formation of a panoramic radar image (PRLI) in real time and transmitting it to the on-board information radio line device, the device 13 generates radio pulses (RI) with linear frequency modulation at the first intermediate frequency, and also provides the formation of quadrature components and digitization of the received signal at the second intermediate frequency.

Block 7 provides operation in the mode specified from the on-board switching apparatus (BKA). In addition to commands from the BCA in the main observation modes, unit 7, through controllers 18-21, receives information from such systems of the spacecraft (satellite 1, 2), such as the onboard time frequency system (UHF), navigation system (SN), and orientation and stabilization system (MTR) ) The required values of the adjustable parameters of the radar devices are set through the code exchange controller 23 (CCO). An exception is the gain control code (RU), which is transmitted to the device 11 through the exchange unit 14. In addition to the actual RU code from the synchronizer 22, an exchange code recording signal is received in the exchange unit 14. In addition, from the synchronizer 22, temporary gates are supplied to the radar device through the device 13, defining a sequence diagram of the operation of the circuits for generating sounding signals and digitizing the received signals during sounding sessions.

The operation of block 7 is carried out under the control of block 15 of the central processor (BCP) according to the programs stored in the program memory. The choice of a work program is carried out by command from the BCA. In BCP 15, an industrial computer board is used, for example, Octagon Systems type 7004.

For BCP 15, all program-accessible resources are conditionally divided into internal and external. The internal resources include the resources of controllers 18-21, and the external resources include the resources of the KRLS devices. Communication with internal subscribers is carried out according to ShAD 17, the formation of which is performed by the internal bus controller 16 from the ISA bus of the BCP 15. Communication with external subscribers is performed using the code exchange controller 23, which provides bi-directional information transfer.

The controller 18 receives pulsed relay control commands from the BCA and transmits them to the BCP 15. Upon receipt of any of the commands, an interrupt request is generated to signal the receipt of a new command. After that, the BCP 15 reads and analyzes the contents of the command registers and thus determines the incoming command.

The controller 19 receives from the on-board time system of the 17-bit serial code of astronomical time (second number of the current day) and converts it into a parallel code for transmission on request to the BTsP 15. Permission or prohibition of interruption is set by the BTsP 15 as a separate bit.

The operation of the synchronizer 22 is based on cyclically repeated (by the number of pulses in a packet) output of a sequence of 23-bit code words. Code words are issued with a clock frequency of 8 MHz. This allows at the same time to generate the necessary codes and strobes in the next sensing session, and to write in the second part of the BCP 15 according to SHAD 17, the necessary sequence of code words for the next sensing session. The number of issued code words N may be in the range from 1 to 2 ¹⁵ .

The launch of the synchronizer 22 for the issuance of code words is carried out by the BCP 15.

The phased antenna system 8 receives control commands of the phase shifters, allowing to form the required field distribution in the elevation plane. Due to this, you can change the shape of the cross section of the chart

directivity of the antenna (BOTTOM) in this plane, namely the width and angular position of the beam.

The parameters of the radiation pattern G _n (□, □) of the antenna system 8 are refined in several stages in the following sequence:

1) an estimated calculation of the DND parameters through the field distribution in the principal planes (in the elevation plane it is specified by the nth combination of phase shifter states);

2) experimental determination of the DND parameters for one section of the waveguide-slotted web on the measuring bench, with subsequent conversion to the DND parameters of the antenna system 8 as a whole;

3) experimental determination of the bottom parameters of the antenna system 8 as part of satellite 1, 2 at the first (technological) stages of operation in orbit using special calibration equipment.

The initial information for the algorithmic and software is a set of step-by-step refinement tables representing the main sections of the DND - azimuthal G _n (□) and elevation G _n (□). The tables contain normalized data on the shape and angular position in the antenna system of 8 coordinates of the main lobe and the nearest lateral for a finite set of combinations of the state of phase shifters (n _max □ 10). The step of the tables provides sufficient accuracy for determining the intermediate values of functions when using linear interpolation. The transition to a two-dimensional DND G _n (□, □) is allowed to be carried out by multiplying one-dimensional for the corresponding values of the angles □ and □.

Block 9 controls the phase shifters of the ZUA of the antenna system 8. Access to the program-accessible resources of block 9 is carried out from the side of block 7 through the channel of the code exchange controller 23.

The minimum allowable interval between two sequentially issued START commands to block 9 is 500 μs, while the antenna beam establishment time is 10 μs from the moment the command was issued.

One of the main functions of the device 13 is to provide all operations for pairing the analog and digital parts of the radar. These operations include:

- the formation of radio pulses (RI) from sequences of samples stored in block 14 exchange in the form of arrays of 16-bit words,

- the formation of the quadrature components of the received signal with the transfer of the spectrum to the second intermediate frequency of 12 MHz and their digitization, followed by transmission to the device 12 digital processing,

- the formation of temporary gates from a sequence of code words received from the synchronizer 22 and their transmission to subscribers.

In the main monitoring modes, the program-accessible resources of the device 13 are used — the control and status register (RUS), the RAM of the RI codes, the RAM address counter (not shown). The number of issued RI samples is determined by the duration of the strobe RI2 coming from the synchronizer 22.

The radio transmitting device 10 transfers the spectrum of the radio pulse (RI) from the first intermediate frequency of 144 MHz to the carrier frequency of 8600 MHz, followed by amplification to a pulse power of P = 1000 W and transmitting it to the antenna system 8 for radiation. In the process of conducting the main observation modes, the device 10 does not require programmed control by the BTSP 15; the control is carried out at the hardware level by the strobe of the synchronizer 22 and the signals of the device 13.

The radio receiver 11 amplifies the received signal from the antenna system 8 and converts it in frequency. The conversion code is received from the synchronizer 22 through the exchange unit 14.

The device 12 in the main observation modes carries out digital processing of the received signal, providing a solution to the following problems:

- refinement of orientation parameters based on the results of sounding sessions in special measuring modes;

- the formation of a panoramic radar image with the given parameters in real time and transferring it to the on-board device of the information radio line accompanied by the necessary service information;

- clarification, as necessary, of the orientation parameters in the process of formation of the pass, not leading to the appearance of gaps in the pass.

The device 12 performs the functions of general control and is involved in data processing, as well as building a satellite data archive based on computer information technologies. As a result, prerequisites are created for turning the electronic collection into a place for redistributing and organizing data.

An uninterrupted exchange of information - remote sensing materials - between satellites 1, 2 and stations 4-6 is carried out via a high-speed radio link. The remote sensing information is received by the antenna 26, and the data of the control and monitoring commands is received by the antenna 25. Block 29 performs initial processing and registration, block 30 decodes and generates information in accordance with the functional features of the remote sensing equipment, block 31 calculates the orbit parameters taking into account information about orbital data. The exchange of information between the equipment of the station occurs on the local network 33, block 34 performs analysis and assessment of the quality of information. The device 35 provides control, and the device 32 stores information.

Satellite 3 provides navigation support for satellites 1, 2 and accelerated circulation of information, which creates the prerequisites for integrating monitoring data into a single system of information resources for Earth exploration from space.

As a result, it is ensured:

- Creation of basic inventory cartographic documentation reflecting the current state and assessment of natural resources;

- mapping dynamics of changes in the natural environment, providing for the updating of inventory maps, the creation of special dynamics and forecast maps, i.e. systematic cartographic monitoring of the state of the environment and its changes caused by the economic activities of people, including changes determined by the objects of the oil and gas industry and the environmental situation in the areas of these objects, the formation of zones of failures and swelling.

- monitoring of ice conditions.

- high detail, simultaneous coverage of vast spaces, the ability to obtain repeated images and study of inaccessible territories.

- great visibility and instantness of the resulting images. They cover vast, including inaccessible, territories at one moment in time and under the same physical conditions. Snapshots provide integrated and

at the same time, a generalized image of all the elements of the earth's surface, which allows us to see their structure and relationships. Monitoring of the results of the system involves not only monitoring the process or phenomenon, but also evaluating it, predicting the spread and development, and in addition, developing a system of measures to prevent dangerous consequences or maintain favorable trends.

A significant increase in efficiency obtained by using this utility model consists in expanding the corporation's ability to receive reliable operational, almost real-time, objective and reliable information.

Claims (6)

1. A corporate system for obtaining space information, including solar-synchronous satellites with multizone optical devices and spectrometers on board, solar-synchronous satellites with synthetic aperture radars and a radio communication channel, devices for determining the orbit parameters, as well as stationary and mobile receiving stations, characterized the fact that spectrometers on board corporate solar-synchronous satellites are made in the form of hyperspectrometers, radars with a synthesized aperture are made s with the possibility of transmitting an interferometric signal, and communication channels - in the form of broadband radio channels with the ability to transmit an interferometric signal to stationary and mobile corporate receiving stations, which are equipped with operational control modes for monitoring and dumping information, and devices for determining the orbit parameters are installed directly on the solar-synchronous satellites. 2. The corporate system according to claim 1, characterized in that at least two corporate solar-synchronous satellites with synthetic aperture radars are formed by a tandem of satellites by synchronizing their radars in phase of the emitted signals with the possibility of obtaining radar images of the earth’s surface simultaneously under different angles, while each of the solar-synchronous satellites is equipped with an on-board switching device, a time frequency system, an orientation and stabilization system controller, MODULES navigation system, bi-directional synchronizer and controller code sharing. 3. The corporate system according to any one of claims 1 and 2, characterized in that it is equipped with at least one corporate geostationary satellite with radio navigation, communication and relay devices connected to solar-synchronous satellites and to stationary and mobile stations. 4. The corporate system according to claim 2, characterized in that the radar with the synthesized aperture of the solar-synchronous satellite comprises a control unit for the observation modes, a phased antenna system, a beam pattern control unit for the antenna system, a radio transmitting and receiving device, a digital processing device, an interface device and information exchange unit. 5. The corporate system according to claim 4, characterized in that the monitoring mode control unit includes a central processor unit, an internal bus controller and an address-data controller connected to the on-board switching device controller, an on-board time frequency system controller, an orientation and stabilization system controller, a controller navigation systems, a synchronizer and a bidirectional code exchange controller, and the antenna system is made with a multi-section, for example a twelve-section waveguide-slotted web. 6. The corporate system according to claim 1, characterized in that the stationary and mobile receiving stations comprise antenna systems, a terminal, high-speed radio line equipment, a primary processing and registration unit, an information generation unit, an orbit parameter calculation unit, an information storage device, a local area network, a unit for analyzing and evaluating information quality; and a control and monitoring device.