The system relates to telemetry, tracking and control of satellites and, in particular, for satellites used in global mobile systems connection, applied cellular technology. EFFECT: providing telemetry, tracking and control (TTC) of satellites of a system for satellite cellular communication systems using one subscriber voice/data communication channel for transmitting TTC data to a satellite and via one satellite to another satellite. To do this, the global positioning receiver (GPS) on board each satellite provides position control signals to the onboard satellite control subsystem and the position receiver reports the current information to the ground station via a cellular subscriber data channel. 2 s. and 17 z.p.f-ly, 3 ill.

The invention relates to telemetry, tracking and control of satellites and, in particular, for satellites used in global mobile communication systems using cellular technology. In modern spacecraft or satellites for satellite systems a TTC transponder is used, which is separate from the user's voice/data communication system for such satellites. These TTC transponders primarily issue control commands sent to the spacecraft from a fixed ground station. Telemetry and tracking information also comes from the spacecraft to the ground station via the TTC transponder. Thus, such communication requires a two-way transponder communication between each satellite and the ground station. Telemetry data coming from the satellite informs the network operator about the position and status of the satellite. For example, the telemetry data may contain information about the remaining propellant of propulsion rockets so that an estimate of the useful life of the satellite can be made. In addition, the critical voltage and current are monitored as telemetry data, which allows the operator to determine whether or not the satellite circuits are operating correctly. Tracking information contains short-term data that allows you to determine the location of the satellite. More specifically, this satellite system uses a TTC transponder on board the satellite to send a tone signal down to the base station to provide the dynamic range and nominal range of the satellite. The height and inclination of the satellite's orbit can be calculated from this information by the ground station operator. The tone signal can be modulated to provide a higher degree of accuracy in determining dynamic range and nominal range. The ground station issues control commands in response to tracking or telemetry data to the satellite, which can be used to adjust the satellite's orbit by turning on the satellite's engine. In addition, other independent control commands may be issued to reprogram the operation of the satellite while controlling other functions of the satellite. TTC information is mainly encoded to eliminate unwanted interference from other operators' signals. In known systems, it has generally only been possible to exchange TTC information with a satellite when the satellite is in line of sight from a fixed ground station. Also known TTC communications were between a particular fixed earth station and its satellite and did not, for example, provide a link to other satellites. TTC transponder links, which are separate from the voice/data channels, are currently used in hundreds of satellites. Separate transponders are mainly used, so the information processed by them is mainly different in origin from the information in the user's communication channels. More specifically, TTC information may be predominantly in digital form, while voice/data communication in some known satellite systems is in analogue form, requiring all available user voice/data channel bandwidth. In addition, the data rate for TTC signals is generally much lower than that of user data. Unfortunately, the use of prior systems having separate transponders for transmitting TTC data leads to some problems. These known systems are not capable of mobile TTC operation. Even in constellations of satellites, when subscriber voice/data channels are interconnected between different satellites, such mobile work TTC, fails due to non-correlation of TTC responders. TTC mobile operations are successful for troubleshooting or for situations where the system operator must be in any of the various locations. Also each satellite has only one TTC transponder. which tends to high price, because it is essential that such a transponder allows reliable control of the satellite by the corresponding ground station. In addition, these transponders use electrical power derived from the onboard power generation system, which typically uses solar cells and batteries. Also, due to the use of separate TTC transponders, the weight of known satellite systems undesirably increases and the cost of manufacturing, testing and launching such satellites into orbit increases. The essence of the invention

Accordingly, it is an object of the present invention to provide a TTC system that uses a voice/data channel to transmit TTC data and therefore does not require a transponder separate from the subscriber's data/voice link equipment. Another goal is to create a TTC system that is suitable for satellites used in global, mobile cell communications missions. In one embodiment of the invention, the control system is included in a satellite communication system having at least one satellite with a transceiver providing a plurality of communication channels for establishing communication between a plurality of subscribers. The control system includes a satellite subsystem on board each satellite and a ground station. The satellite subsystem manages the functions of the satellite. One of the subscriber's communication channels is connected to the ground station and to the satellite control subsystem to establish a TTC connection, so that commands can be transmitted to the satellite control subsystem, which responds by controlling a given satellite function. The control system also includes a sensor block on board the satellite to measure the specified modes on the satellite and to provide transmission of telemetry data via the subscriber's communication channel to the ground station. In addition, the control system may also include a position receiver on board the satellite to track and provide current satellite data. The current data is fed over the subscriber's communication channel so that the current data is sent from the satellite to the ground station. Also, current data can be fed to the satellite control subsystem to provide automatic onboard control of the satellite's heading. FIG. 1 shows a mesh pattern generated by a single satellite in a multi-satellite mesh communication system, FIG. 2 shows a cross-talk between a ground control station and a plurality of satellites, FIG. 3 shows a block diagram electronic system for ground control station and satellite. Satellite 10 comprises a plurality of user data transmitter-receiver combinations, hereinafter referred to as transceivers, solar receivers 12, transmit antennas 14, and receive antennas 16. The transceiver transmitters use individual transmit antennas 14 to simultaneously radiate a plurality of moving cells forming a pattern 18 over a portion of the Earth's surface. Each individual cell, such as cell 20 in diagram 18, also contains airspace above the Earth and can be characterized as a conical cell. The system operator of ground station 22, although mobile, is generally considered to be a fixed point on earth relative to a fast moving satellite 10 that can travel at 17,000 miles per hour. The cells are always in motion because the satellite 10 is continuously moving. This is in contrast to terrestrial mobile cellular systems, in which the cells are generally considered to be fixed and the mobile subscriber moves through the cells. As the cell moves towards the subscriber, the cell switch must "transfer" the connection of the subscriber to the adjacent cell. If the satellites are all moving in the same direction and have substantially parallel low polar orbits, the adjacent cell pattern and/or adjacent cell can be predicted by the cell switch with a high degree of accuracy. The amplitude information or the binary error information may be used to perform the switching. Each satellite diagram of a cellular system may use multiple clusters of four cells. One cluster contains cells 24, 26, 20 and 28, where the cells operate at frequencies having values ​​respectively designated A, B, C and D. Nine such nodes are shown in figure 1 and they form a diagram 18. By reusing frequencies A, B, C, and D divide the amount of spectrum that would be required to link to Diagram 18 by about nine. One of the transceivers of satellite 10, for example, may use an uplink frequency of 1.5 gigahertz (GHz) to 1.52 GHz, and an uplink frequency of 1.6 to 1.62 GHz. Each cell pattern 18 can be set to 250 nautical miles in diameter and it may take 610 seconds to process a full cell pattern of a satellite mesh system. The cell frequency spectrum may be selected as suggested by the standards published by the Electronic Industries Association (EIA) for terrestrial cell system coding. Subscriber communication channels use digital technology to transmit voice and/or factual information from one subscriber to another. In accordance with the exemplary embodiment described, control station 22 located in frequency "A" cell 24 transmits TTC information to satellite 10 using one of the voice/data cell consumer channels instead of a separate TTC transceiver. Each of these meshed subscriber channels is a single voice/data line, identified by a route or telephone number. Typically, these channels begin and end at the surface of the Earth. However, when used as a TTC, the link termination of the channel and the "call" receiver may be satellite 10. Each satellite in a node receives a single number (ie, a phone number). Ground station 22 can communicate directly with any satellite it is in view of by generating the address of the satellite. Similarly, ground station 22 also has a single address. If satellite 10 is moving in the direction of arrow 30 such that cell 26 will move next above operator 22, cell "A" 24 will go to cell "B" 26, which will later "go to" cell "D" 32, for example. If cell 26 goes down, TTC communication will only be temporarily interrupted and not completely broken, as is the case with known systems having only one TTC transponder per satellite. Therefore, the cell system shown in FIG. 1, provides a high degree reliability for the TTC exchange, due to the redundancy of the transceivers providing each cell. As shown in FIG. 2, ground station 50 may provide TTC information to line-of-sight satellite 52 over subscriber channel 51. Satellite 52 receives and sends TTC from station 50 along with subscriber multiplex data channels, such as from subscriber 53 over channel 55. The cell switch recognizes the satellite identifier or address for satellite 52 in the same way that the network recognizes terrestrial designations. Also, if it is necessary to pass the TTC data to another satellite 54 that is not in line of sight of station 50, then this data can be sent to satellite 52 and then transmitted over link 56 to satellite 54. Similar arrangements can be made for all network additions and TTC data to each satellite and from each satellite in the network. If it is necessary to report the status of the satellite 58 and the data of the position receiver to the ground control station 50, it generates a call signal and passes the data on line 60 using the only number for the satellite 52. The TTC information is then transmitted to the Earth on channel 51 to the control station 50. Typically satellite types 52, 54 and 58 are interrogated for TTC data, and serious events affecting the health of any given satellite are generated and sent by that satellite via other satellites, if necessary, to the control station. Thus, the system allows continuous transmission of TTC data to and from the control station 50, even if the control station 50 is not in the line of sight of the satellite in communication. FIG. 3 shows block diagrams of ground station 100 and satellite 102. Ground station 100 can be either a fixed permanent station or mobile subscriber using a computer with a modem to communicate via standard phone . Encoder 103 provides a "address" signal to transmitter 105. Transceiver line 104 carries signals from transmitter 105 of control station 100 to antenna subsystem 106 of satellite 102. Receiver 108 of satellite 102 is coupled between antenna subsystem 106 and demodulator/demultiplexer system 110. Router 112 is connected between the output of system 100 and the input of multiplexer/modulator 114. Router 112 also processes the addresses of all incoming data and sends appropriately addressed data to other satellites, for example, through multiplexer/modulator 114, which is also connected to the two-way transceiver subsystem 116. Router 112 encodes the appropriate addresses into signals having destinations other than satellite 102. Router 112 sorts out any messages for satellite 102 that are designated by their address code. The position receiver 118 of the global installation satellite (GPS) is connected to the router 112 through the conductor 120 and to the satellite subsystem 122 through the conductor 124. The router 112 is connected to the satellite control subsystem 122 through the conductor 126 and to the sensor subsystem 128 through the conductor 130. Satellite subsystem 122 through the conductor 122 decrypts command messages from router 112 to satellite 102 and causes certain actions to be taken. The sensor subsystem 128 provides telemetry data to the router 112. The global positioning system (GPS) position receiver 118 receives information from existing satellites (GPS) in a known manner and determines the exact position of the satellite 102 in space. Orbital space vectors are derived from this information. The position receiver 118 also determines the position of the satellite 102 relative to the GPS constellation. This information is compared with the target position information stored in the router 112. Error signals are generated by the GPS position receiver 118 and sent to the satellite control subsystem 122 for automatic heading correction. The error signal is used in the satellite control subsystem 122 to control small rockets that play the role of "heading". Therefore, satellite 102 uses GPS information to steer its own heading, not just to receive heading control from station 100. This on-board control allows satellite 102 to be positioned and monitored within a few meters. The GPS position receiver 118 also generates space vectors to the router 112, and the sensor subsystem 128 provides other telemetry information over wire 130 to router 112, which composes messages that are fed over wire 132 to multiplexer/modulator 114 and over wire 134, transmitter 136 and conductor 138 - for transmission by the antenna subsystem 106. These messages are then transmitted over link 140 to receiver 108 of ground station 100. Alternatively, when it is necessary to communicate with another control station on another satellite link, messages composed by router 112 are sent through a two-way transceiver subsystem 116. In this way, each satellite can "know "his position, as well as the position of his neighbors in the constellation. The ground operator also has constant access to this current information. Therefore, unlike known systems that do not include GPS position receivers, tracking or current information for satellite 102 is computed on board satellite 102. Satellite 102 does not need to have permanent trajectory corrections from ground station 100. However, trajectory control information is provided from ground station 100 when needed. The GPS signal is a digital signal that is compatible with digital cell lines or channels used for terrestrial subscriber-to-subscriber communications. Onboard digital format capture GPS signal allows the following information to be inserted into channels normally used for the transmission of voice and/or factual information. The system has many advantages over known systems that use a separate TTC transponder in each satellite. Namely, if the transponder in a known system fails, the satellite becomes useless. Otherwise, since ground station 22 in Figure 1, for example, can use any of the transceivers associated with satellite 10, even if one of these transceivers fails, there are still 35 others with which station 22 can communicate. TTC with satellite 10. In addition, as shown in FIG. 2, even if all satellite-to-Earth communications of a particular satellite, for example 58, fail, the ground station 50 will be able to communicate with that satellite using two-way communication, for example, 60 through another satellite, for example 52. Thus, the system of the invention provides a reliable TTC connection.

Also, the TTC system can be in constant communication with a particular satellite through two-way communication, rather than waiting for a line of sight, as in some known TTC systems. Known TTC systems require the ground station to be fixed, while mobile ground control stations can be used for this system. A mobile earth station has a single address or telephone number assigned to it, and the position of the earth station can be monitored in the same way as subscribers are monitored from satellites of cell satellite constellations. This tracking system uses a GPS receiver on board the satellite to provide on-board tracking and tracking control, not just ground tracking control. This digital tracking information is immediately entered into the subscriber's digital cellular channel.

CLAIM

1. A control system for a satellite communication system having at least one satellite with receivers and transmitters that create a plurality of subscriber communication channels to establish communication between a plurality of subscribers, containing a satellite control subsystem on board the satellite to control the functions of the satellite, a ground control station, the first line communication connected to the satellite control subsystem and the ground control station for connecting the ground control station with the satellite control subsystem, characterized in that the connection providing communication is established through one of the subscriber communication channels, while the specified one of the subscriber communication channels is used to transmit commands to the satellite a control subsystem combined with a plurality of subscriber communication channels, wherein the satellite includes a plurality of transmitters and receivers for projecting a plurality of adjacent cells to the Earth, and the satellite control subsystem is sensitive to commands I will give the ground control station to enable control of these commands by the selected function of the satellite. 2. The control system according to claim 1, characterized in that the first communication line comprises a ground control station transmitter and a coding means connected to the ground control station transmitter for encoding a given satellite address code in commands for the satellite, and the satellite contains a demodulator / demultiplexer connected with a satellite receiver, and a router for recognizing and responding to a given satellite address code for issuing commands and connected to the satellite control subsystem and the demodulator / demultiplexer for connecting the satellite control subsystem to the demodulator / demultiplexer with the ability to receive commands from the satellite control subsystem from the ground control station. 3. The control system according to claim 1, characterized in that the satellite contains a sensor subsystem for measuring a given mode on the satellite and issuing telemetry data, a second communication line for connecting the sensor subsystem to the specified one of the subscriber communication channels for transmitting telemetry data from the satellite to the ground control station. 4. The control system according to claim 3, characterized in that the second communication line contains a router connected to the sensor subsystem, and the router encodes the telemetry data with an address code corresponding to the ground control station, and outputs the encoded telemetry data by means of a satellite transmitter through the specified one of the subscriber communication channels. 5. The control system according to claim 1, characterized in that the satellite contains a position receiver for monitoring and issuing current satellite data, a second communication line for issuing current satellite data through the specified one of the subscriber communication channels from the satellite to the ground control station. 6. The control system according to claim 5, characterized in that the second communication line contains a router connected to the position receiver, and the router encodes the specified telemetry data with an address code corresponding to the ground control station, and connected to a transmitter that is part of the satellite, and the transmitter provides transmission of current data to the ground control station through the specified one of the subscriber communication channels. 7. Control system according to claim 1, characterized in that the ground control station is mobile. 8. The control system according to claim 1, characterized in that the satellite communication system contains a plurality of satellites, and each satellite contains a transceiver subsystem, in which the satellites are connected by two-way communications through transceiver subsystems, so that they establish subscriber communication channels with each other and allow terrestrial control stations to send commands via one of the subscriber communication channels to one of the plurality of satellites through another of the plurality of satellites having two-way communication with it. 9. The control system according to claim 1, characterized in that the satellite communication system further comprises a cell switch connected to the first communication line for sending a plurality of subscriber messages over the specified subscriber communication channels. 10. The control system according to claim 1, characterized in that the satellite further comprises a plurality of transmitters and receivers for projecting a plurality of adjacent cells that move in connection with the satellite relative to the surface of the Earth, and each of the transmitters and receivers has the ability to transmit and receive on one of cells via one of the subscriber communication channels, and a multiplexer/modulator for switching communication with the ground control station between transmitters and receivers associated with each of the cells to ensure continuous issuance of commands to the satellite for at least a specified period of time when the satellite is in line of sight ground control station. 11. A telemetry, tracking and control system for satellite cellular communication systems, having a plurality of satellites, each of which has transmitters and receivers that create a plurality of subscriber communication channels to establish communication between a plurality of subscribers, containing on each satellite a satellite control subsystem to control the functions of this satellite, a position receiver for determining the position of this satellite, a ground control station and a first communication line connected to the satellite control subsystem, a position receiver and a ground control station, characterized in that the communication connection is established through one of the subscriber communication channels, while the ground station control uses the specified one of the subscriber communication channels to transmit commands to the satellite control subsystem and receive data from the position receiver. 12. The telemetry, tracking and control system according to claim 11, further characterized in that it contains a router connected to the position receiver and the satellite control subsystem for connecting the position receiver to the satellite control subsystem, and the position receiver is configured to issue heading control signals to the satellite a control subsystem to control the satellite's heading, and the satellite control subsystem is responsive to commands from the ground control station to allow control of those commands by the selected function of the satellite. 13. The telemetry, tracking and control system according to claim 11, characterized in that the first communication line contains a transmitter of a ground control station, a coding means connected to the transmitter of a ground control station for encoding a given address code in commands for a satellite, each satellite contains a demodulator / demultiplexer connected to the satellite receiver, and a router for recognizing and responding to a given address code for issuing commands, connected to both the satellite control subsystem and the demodulator / demultiplexer for connecting the satellite control subsystem to the satellite receiver with the ability to receive commands from the satellite control subsystem from the ground control stations. 14. The telemetry, tracking and control system according to claim 11, characterized in that it contains on each satellite a sensor subsystem for measuring a given mode on the satellite and issuing telemetry data, the sensor subsystem being connected to a router connected to a transmitter and a first communication line for connection sensor subsystem with a ground control station through the specified one of the subscriber communication channels with the possibility of sending telemetry data from the satellite to the ground control station. 15. The telemetry, tracking and control system according to claim 14, characterized in that it contains a router connected to the sensor subsystem for encoding said telemetry data with an address code corresponding to the ground control station. 16. Telemetry, tracking and control system according to claim 11, characterized in that the ground control station is mobile. 17. The telemetry, tracking and control system according to claim 11, characterized in that the satellite communication system contains a plurality of satellites, each of which contains a transceiver subsystem, and the satellites are connected by two-way communications through transceiver subsystems, so that they establish subscriber communication channels with each other and allowing the ground control station to send commands via the specified one of the subscriber communication channels to one of the plurality of satellites through another of the plurality of satellites having two-way communication with it. 18. The telemetry, tracking and control system according to claim 11, characterized in that the satellite communication system further comprises a cellular switch connected to the first communication line for sending a plurality of subscriber messages over the specified subscriber communication channels. 19. The telemetry, tracking and control system according to claim 11, characterized in that the satellite communication system further comprises a plurality of transmitters and receivers for projecting a plurality of adjacent cells that move in connection with the satellite relative to the surface of the Earth, each of the transmitters and receivers is made with the possibility of transmitting and receiving to one of the cells through one of the subscriber communication channels and a multiplexer / modulator for switching communication with the ground control station between the transmitter and receiver associated with each of the cells with the possibility of continuously issuing commands to the satellite for at least a specified period of time when the satellite is in direct line of sight of the ground control station.

Tomorrow the whole world celebrates Cosmonautics Day. April 12, 1961 Soviet Union For the first time in history, he launched a manned spacecraft on board which was Yuri Gagarin. Today we will show how the second Kazakh telecommunications satellite KazSat-2 (KazSat-2) was launched from the Baikonur Cosmodrome at the end of 2011 using the Proton-M launch vehicle. How was the device launched into orbit, what condition is it in, how and from where is it controlled? We learn about it in this photo essay.

1. July 12, 2011. The heaviest Russian space rocket "Proton-M" with the Kazakh communication satellite No. 2 and the American SES-3 (OS-2) is being taken to the starting position. Proton-M is launched only from the Baikonur Cosmodrome. It is here that the necessary infrastructure exists to service this most complex rocket and space system. The Russian side, namely the manufacturer of the device, the Khrunichev Space Center, guarantees that KazSat-2 will last at least 12 years.

Since the signing of the agreement on the creation of the satellite, the project has been revised several times, and the launch itself has been postponed at least three times. As a result, KazSat-2 received a fundamentally new element base and a new control algorithm. But most importantly, the satellite was equipped with the latest and very reliable navigation instruments manufactured by the French concern ASTRIUM.

This is a gyroscopic angular velocity vector meter and astro sensors. With the help of astro sensors, the satellite orients itself in space by the stars. It was the failure of navigation equipment that led to the fact that the first KazSat was actually lost in 2008, which almost caused an international scandal.

2. The path of the rocket with the power supply and temperature control systems connected to it for the head part, where the Breeze-M upper stage and satellites are located, takes about 3 hours. The speed of movement of a special train is 5-7 kilometers per hour, the train is served by a team of specially trained drivers.

Another group of spaceport security personnel inspects the railroad tracks. The slightest non-calculated load can damage the rocket. Unlike its predecessor, KazSat has become more energy intensive.

The number of transmitters has increased to 16. There were 12 of them at KazSate-1. And the total power of transponders was increased to 4 and a half kilowatts. This will allow you to pump an order of magnitude more all kinds of data. All these changes were reflected in the cost of the device. It amounted to 115 million dollars. The first device cost Kazakhstan 65 million.

3. The inhabitants of the local steppe are calmly watching everything that happens. ships of the desert)

4. The size and capabilities of this rocket are truly amazing. Its length is 58.2 meters, the weight in the filled state is 705 tons. At the start, the thrust of 6 engines of the first stage of the launch vehicle is about 1 thousand tons. This makes it possible to launch objects weighing up to 25 tons into a reference near-Earth orbit, and up to 5 tons into high geostationary (30 thousand km from the Earth's surface). Therefore, Proton-M is indispensable when it comes to launching telecommunications satellites.

There are simply no two identical spacecraft, because each spacecraft is a completely new technology. In a short period, it happens that you have to change completely new elements. “KazSate-2” applied those new advanced technologies that already existed at that time. Part of the European-made equipment was delivered, in the part where we had failures at KazSat-1. I think that the equipment that we currently have at KazSat-2 should show good results. It has a fairly good flight history.

5. There are currently 4 launch sites for the Proton launch vehicle at the cosmodrome. However, only 3 of them, at sites No. 81 and No. 200, are in working order. Previously, only the military was engaged in launching this rocket due to the fact that working with toxic fuel required hard command guides. Today, the complex has been demilitarized, although there are a lot of former military men who have taken off their shoulder straps in the combat crews.

The orbital position of the second "KazSat" has become much more convenient for work. This is 86 and a half degrees east longitude. The coverage area includes the entire territory of Kazakhstan, part of Central Asia and Russia.

6. Sunsets at the Baikonur Cosmodrome are exceptionally technological! A massive structure just to the right of the center of the picture is a Proton-M with a maintenance farm connected to it. From the moment the rocket was taken to the launch site of site No. 200, and until the moment of launch, 4 days pass. All this time, the preparation and testing of the Proton-M systems has been carried out. Approximately 12 hours before the launch, a meeting of the state commission is held, which gives permission to refuel the rocket with fuel. Refueling starts 6 hours before the start. From this moment on, all operations become irreversible.

7. What is the benefit of our country having its own communications satellite? First and foremost is problem solving. information support Kazakhstan. Your satellite will help expand the range of information services for the entire population of the country. This is an e-government service, the Internet, mobile communications. Most importantly, the Kazakh satellite will allow us to partially refuse the services of foreign telecommunications companies that provide relay services to our operator. We are talking about tens of millions of dollars, which will now go not abroad, but to the country's budget.

Victor Lefter, President of the Republican Center for Space Communications:

Kazakhstan has a fairly large territory compared to other countries. And we must understand that we will not be able to provide communication services that are limited by means of cable and other systems to every locality, to every rural school. The spacecraft solves this problem. Almost the entire area is closed. Moreover, not only the territory of Kazakhstan, but also part of the territory of neighboring states. And satellite is a stable communication capability

8. Various modifications of the Proton launch vehicle have been in operation since 1967. Its chief designer was Academician Vladimir Chelomey and his design bureau (currently, Salyut Design Bureau, a branch of the M.V. Khrunichev GKNPTs). We can safely say that all the impressive Soviet projects for the development of near-Earth space and the study of objects in the solar system would not have been feasible without this rocket. In addition, the Proton is distinguished by a very high reliability for equipment of this level: for the entire period of its operation, 370 launches were made, of which 44 were unsuccessful.

9. The only and main drawback of the “Proton” is the extremely toxic components of the fuel: asymmetric dimethylhydrazine (UDMH), or as it is also called “heptyl” and nitrogen tetroxide (“amyl”). In places where the first stage fell (these are territories near the city of Dzhezkazgan), pollution occurs environment which requires costly cleaning operations.

The situation was seriously aggravated in the early 2000s, when three launch vehicle accidents occurred in a row. This caused extreme dissatisfaction with the authorities of Kazakhstan, who demanded large compensations from the Russian side. Since 2001, the old modifications of the launch vehicle have been replaced by the modernized Proton-M. It stands digital system control, as well as a system for bleeding unburned fuel residues in the upper layers of the ionosphere.

Thus, it was possible to significantly reduce the damage to the environment. In addition, a project has been developed, but still remains on paper, for an environmentally friendly Angara launch vehicle, which uses kerosene and oxygen as fuel components, and which should gradually replace the Proton-M. By the way, the Angara launch vehicle complex at Baikonur will be called Baiterek (Topol in Kazakh).

10. It was the reliability of the rocket that attracted the Americans at the time. In the 90s, the ILS joint venture was created, which positioned the rocket in the American telecommunications systems market. Today, most US civil communications satellites are launched by Proton-M from a cosmodrome in the Kazakh steppe. The American SES-3 (owned by SES WORLD SKIES), which is located in the head of the rocket along with the Kazakh KazSat-2, is one of the many launched from Baikonur.

11. In addition to the Russian and American flags, the rocket carries the Kazakh flag and the emblem of the Republican Center for Space Communications, the organization that today owns and operates the satellite.

12. July 16, 2011, 5 hours 16 minutes and 10 seconds in the morning. Climax moment. Fortunately, everything goes well.

13. 3 months after launch. Young specialists are Bekbolot Azaev, the leading engineer of the satellite control department, as well as his colleagues, engineers Rimma Kozhevnikova and Asylbek Abdrakhmanov. These guys are running KazSat-2.

14. Akmola region. The small, and until 2006, unremarkable regional center Akkol became widely known 5 years ago, when the first MCC in the country was built here - the center for controlling the flights of orbital satellites. October here is cold, windy and rainy, but right now the hottest time is coming for those people who should give the KazSat-2 satellite the status of a full-fledged and important segment of Kazakhstan's telecommunications infrastructure.

15. After the loss of the first satellite in 2008, the Akkol Space Communications Center underwent a major upgrade. It allows you to control two devices at once.

Baurzhan Kudabaev, Vice President of the Republican Center for Space Communications:

A special software new equipment has been delivered. Before you stand command-measuring system. This is the delivery of the American company Vertex, as it was at KazSat-1, but a new modification, an improved version. The developments of the company "Russian Space Systems" were applied. Those. these are all developments of today. New programs, equipment element base. All this improves the work with our spacecraft.

16. Darkhan Maral, head of the flight control center at the workplace. In 2011, young specialists, graduates of Russian and Kazakh universities, came to the Center. They have already been taught how to work, and according to the leadership of the RCKS, there are no problems with personnel replenishment. In 2008, the situation was much worse. After the loss of the first satellite, a significant part of highly educated people left the center.

17. October 2011 was another high point in the work on the Kazakh satellite. Its flight design tests were completed, and the so-called test tests began. Those. it was like an exam for the manufacturer on the functionality of the satellite. Everything happened as follows. A television signal was raised at KazSat-2.

Then several groups of specialists went to different regions of Kazakhstan and measured the parameters of this signal, i.e. how well the signal is relayed by the satellite. There were no comments, and in the end, a special commission adopted an act on the transfer of the satellite to the Kazakh side. Since that moment, Kazakh specialists have been operating the device.

18. Until the end of November 2011, she worked at the Akkol Space Center large group Russian specialists. They represented subcontractors under the KazSat-2 project. These are the leading companies in the Russian space industry: Center im. Khrunichev, who designed and built the satellite, the Mars Design Bureau (which specializes in the navigation of orbiting satellites), as well as the Russian Space Systems Corporation, which develops software.

The whole system is divided into two components. This is, in fact, the satellite itself and the ground control infrastructure. According to the technology, the contractor must first demonstrate the operability of the system - this is the installation of equipment, its debugging, demonstration functionality. After all the procedures - training of Kazakhstani specialists.

19. The Space Communications Center in Akkol is one of the few places in our country where a favorable electromagnetic environment has developed. There are no radiation sources for many tens of kilometers around here. They can interfere with and interfere with satellite control. 10 large parabolic antennas are directed into the sky at one single point. There on long distance From the surface of the Earth - more than 36 thousand kilometers - hangs a small man-made object - the Kazakh communications satellite "KazSat-2".

Most modern communications satellites are geostationary. Those. their orbit is built in such a way that it seems to hover over one geographical point, and the rotation of the Earth has practically no effect on this stable position. This allows using the onboard repeater to pump large amounts of information, to confidently receive this information in the coverage area on Earth.

20. Another curious detail. According to international rules, the permissible deviation of the satellite from the standing point can be a maximum of half a degree. For MCC specialists - keep the device in given parameters- jewelry work, requiring the highest qualifications of ballistics specialists. The center will employ 69 people, 36 of them are technical specialists.

21. This is the main control panel. There is a large monitor on the wall, where all the telemetry flows, on a semicircular table there are several computers, telephones. Everything seems to be very simple...

23. Victor Lefter, President of the Republican Center for Space Communications:
- We will expand the Kazakh flotilla to 3, 4, and possibly even up to 5 satellites. Those. so that there is a constant replacement of devices, there is a reserve, and so that our operators do not experience such an urgent need to use products from other states. So that we can be provided with our reserves.”

24. Currently, satellite control is backed up from Moscow, where the Space Center named after. Khrunichev. However, the Republican Center for Space Communications intends to reserve a flight from Kazakhstan. For this, a second MCC is currently being built. It will be located 30 kilometers north of Almaty.

25. The National Space Agency of Kazakhstan plans to launch the third satellite KazSat-3 in 2013. The contract for its development and production was signed in 2011 in France, at the aerospace show in Le Bourget. The satellite for Kazakhstan is being built by NPO named after academician Reshetnev, which is located in the Russian city of Krasnoyarsk.

26. Operator interface of the control department. This is how he looks now.

In the video you can see how this satellite was launched.

Original taken from here

Read our community also on VKontakte, where there is a huge selection of videos on the topic "how it's done" and on Facebook.

Satellite command and control systems (SSU and K) are a combination of radio technical means control and management of the movement and modes of operation of the onboard equipment of satellites and other spacecraft. SU&K includes ground and airborne radio equipment.

The ground part consists of a network of command and measurement posts (CIP), a coordination and computing center (CCC) and a central control center (CCC), interconnected by communication lines and data transmission.

The instrumentation network is necessary, firstly, because the visibility zone of moving satellites from one instrumentation located on the Earth's surface is limited in space and time, and secondly, the accuracy of determining the parameters of the movement of an artificial satellite from one instrumentation is insufficient, the more independent measurements will be carried out , the higher the accuracy. Continuous monitoring of each satellite requires the use of a network of several dozen instruments (some of them can be located on ships, aircraft, and satellites).

Since control commands and measurement results must be transmitted over long distances, communication lines apply various methods improve noise immunity. These methods can be divided into 3 groups.

The first group consists of operational measures aimed at improving the quality indicators of communication channels used for data transmission. These include: improving channel characteristics; reducing the number of impulse noise occurring in the channels, preventing interruptions, etc.

The second group includes measures aimed at increasing the noise immunity of the elementary data signals themselves, for example, such as:

Increasing the signal-to-noise ratio by increasing the signal amplitude;

Application of various methods of accumulation and diversity of signals;

The use of a more noise-resistant type of modulation and more advanced methods of demodulation and registration of elementary signals (integrated reception, synchronous detection, the use of noise-like signals (NLS), etc.)

Some of these methods provide an increase in noise immunity to the entire complex of interference (for example, accumulation, switching to another type of modulation, others to certain types of interference. For example, NPN and interleaving provide protection against error bursts, but do not increase noise immunity to independent errors.

The third group of measures to improve the reliability of digital information transmitted over communication channels includes various methods that use the information redundancy of code symbols that display the transmitted data at the input and output discrete channel(noise-immune coding, questioning, etc.). The implementation of these methods requires the use of special equipment:

Error protection devices (RCD) - conversion of code symbols at the input and output of the communication channel.

According to the method of introducing redundancy, there are:

RCDs with permanent redundancy, which use corrective codes that detect and correct errors;

RCDs with variable redundancy, which use feedback on the opposite channel;

Combined RCDs using feedback in combination with code and indirect methods for detecting and correcting errors.

In an RCD with variable redundancy, errors are determined either by applying corrective codes or by comparing the code symbols transmitted and received over the reverse channel. Error correction occurs when a corrupted or dubious code word is retransmitted. In combined RCDs, part of the errors or erasures is corrected due to the constant redundancy of the code, and the other part is only detected and corrected by retransmission.

By correcting errors in RCDs with constant redundancy, it is possible to achieve almost any required values ​​of reception reliability, however, in this case, the correction code must have very long code blocks, which is associated with error packetization from real channels.

RCDs with feedback and combined RCDs have received the widest application in data transmission systems. The redundancy in the forward channel is relatively small, since. used only for error detection or correction of low multiplicity errors. When errors are detected, redundancy is increased by retransmission of corrupted data blocks.

In practice, error detection is widely used cyclic codes for which both international and domestic standards have been developed. The most widely used cyclic code with a generating polynomial This code is a cyclic version of Hamming's extended when (added general check parity), its length and code distance d=4. It is known that the detecting ability of a code increases with increasing code distance. Therefore, on channels of medium and low quality, codes with d>4, which, with an approximate reduction in the maximum length of the codeword, naturally leads to an increase in the number of check symbols. The so developed standard recommends the following generator polynomial , which defines a cyclic BCH code with a minimum code distance of 6 and a length of no more than bits. The widespread use of cyclic codes (Hamming, BCH) for error detection is largely due to the simplicity of their implementation.

Everything said above concerned mainly the use of codes for error detection. It is known that it is possible to significantly improve the performance of the callback transmission method by introducing error correction into it. The code in this case is used in the mode of partial error correction, and the requery is carried out if it is impossible to decode the received sequence.

In cases where, for one reason or another, it is impossible to create a channel feedback or the callback delay is unacceptable, one-way data transmission systems with error correction by redundant codes are used. Such a system, in principle, can provide any required confidence value, however, the correction code must have very long code blocks. This circumstance is due to the fact that errors are packetized in real channels, and packet lengths can reach large values. To correct such error packets, it is necessary to have blocks of significantly greater length.

Currently, a large number of codes are known that correct packets of errors. A typical approach is to solve this problem with methods that allow you to correct long bursts of errors by not detecting some combination of random errors. This uses cyclic codes such as Fire codes and decoders such as the Meggit decoder. Together with suitable interleaving, block or convolutional codes are used to correct random errors. In addition, there are methods that allow you to correct long packets in the sentence that there is a sufficiently long error-free zone between two packets.

The composition of the instrumentation usually includes several command and measuring stations: receiving and transmitting. These can be powerful radars designed to detect and monitor “silent” satellites. Depending on the frequency range used, instrumentation can have parabolic and helical antennas, as well as antenna systems that form an in-phase antenna array to form the necessary beam pattern.

Structural scheme typical instrumentation consisting of one transmitting and several receiving stations is shown in Figure 4.7.

The high-frequency oscillation received by each antenna (A) after amplification in the receiver (PR) enters the channel separation equipment (ARC), in which the signals of triple measurements (RTI), radiotelemetry measurements (RTI), television (STV) and radiotelephone communications (RTF) are separated . After processing these signals, the information contained in them enters either the computer complex (CM) or directly to the display and recording equipment (AORI), from where it is broadcast to the control point (CP).

Commands for controlling the movement of satellites are formed on the control panel, which are transmitted through a software-temporary device (PTD) and channel separation equipment (ARC) to the corresponding satellite at the moments of its radio visibility from this instrument (it is also possible to transfer to other instrumentation, in the visibility zone of which there are satellites) .

Figure 4.7 - Structural diagram of a typical instrument

In addition, the data in the digital computer and AORI is transmitted via a data transmission line (DLD) to the coordinate computing center of the SSU and K. To link the operation of the instrumentation to the universal time system, it includes a local point of this system (MP), a special receiving device of which receives time signals.

The block diagram of the satellite onboard equipment is shown in Figure 4.8.

Figure 4.8 - Structural diagram of the satellite onboard equipment

The onboard equipment of the artificial satellite contains a receiving-transmitting device (P and PR) and antenna device(AU) with antenna switch (AP). AU can consist of several directional and non-directional antennas.

The most important element of the AES equipment is the onboard computer, which receives both signals from the channel separation equipment (ARC) of the command transmission system (CTS), and from all sensors of the telemetric change system (RTI). In the on-board computer, commands are formed for the trajectory measurement system (RSTI), the RTI system and the radio control system (SRU). Airborne radio beacons are part of the trajectory measurement system (RSTI), the signals of which are fed through the onboard channel separation equipment (BRK) to onboard transmitters (P).

The time scale of satellites and all ground-based instrumentation is coordinated using the on-board time standard (BET), which is periodically checked against the ground-based universal time system.

At the stage of orbit correction, the RSTI functions depend on the adopted satellite control method. With the corrective method, new orbital parameters are calculated, and then the onboard corrective engines are switched on at the calculated time point; with the servo control method, the results of trajectory measurements are immediately used to calculate the current deviations of the actual coordinates of the satellite and its speed (possibly also orientation) from the required ones and the calculated parameters are corrected in throughout the entire maneuver. Tracking control is used where high maneuvering accuracy is required.

Trajectory measurements use the same methods for measuring slant range, radial velocity and angular coordinates as used in radio navigation systems (Section 2) or motion control systems (Section 3).

The main feature of the satellite onboard equipment is the combination of radio engineering systems in order to reduce its mass, reduce dimensions, increase reliability and simplify. Trajectory measurement systems are combined with television and telemetry systems, radio control systems with communication systems, etc. This imposes additional restrictions on the choice of modulation and coding methods in channels various systems, allowing to separate the corresponding information flows.

Let us consider the structure of modern on-board systems for radiotelemetry and trajectory measurements and the features of their operation in combined radio links.

The block diagram of the onboard equipment (RTI) is shown in Figure 4.9.

RTI is a multi-channel information-measuring system, which includes a large number of sources of primary information (OR) and the corresponding number of sensors - converters (D). As such sensors, various converters of non-electrical quantities into electrical quantities are used (in a form convenient for processing and storage): for example, parametric sensors, which include resistive, capacitive, magnetic-elastic, electrostatic, etc. Of the resistive converters, potentiometric, tensometric and thermistor. With the help of such sensors, it is possible to measure linear and angular displacements, elastic deformation of various elements of the satellite structure, temperature, etc.

Figure 4.9 - Structural diagram of the RTI onboard equipment

The use of analog-to-digital converters (ADC) allows you to immediately receive the measured information in digital form and send it to a computer or memory device (memory). To protect information from internal interference and failures in the UPI (device for primary information processing), noise-immune coding is carried out and oscillatory signals (ICS) and time stamps from the BEV are introduced to identify the signal of each sensor.

For the exchange of information between the elements of the RTI system, a single data bus is used, which provides greater flexibility of control within the system and combined systems. As part of the RTI, an on-board interface device (BUS) is also used, which ensures the pairing of all RTI elements in terms of data formats, transmission speed, connection order, and so on. BUS works together with the ARC, which forms digital signal for the transmitter (P).

The internal control complex, the structure of which is shown in Figure 4.10, also uses a common data bus, computer, memory and BEV.

Figure 4.10 - Internal control complex

The onboard control complex (OCC) is part of the automated control system of the artificial satellite. In accordance with the computer program, the BKU, on commands from the Earth, controls the movement of the satellite in orbit, switches the operating modes of the onboard equipment, replaces failed units, etc. In autonomous mode, the BCU controls the orientation of the satellite and, based on the signals from the orientation sensors (OS), stabilizes the position of the satellite in space.

The received signal is amplified in the receiver (PR), after demodulation, the group signal enters the ACR, in which the signals are distinguished: the control system for equipment units (SUB), the systems for separating and transmitting commands to control the means of changing the position of the satellite (ARC SPK). Each instruction is assigned an address, a value, and an execution time; the address indicates the control object: SP - means of moving satellites; SC - means of correcting the orientation of a satellite, etc.

The most important for a satellite are commands to change its orbit; orientation relative to the Earth or the Sun and its stabilization relative to these directions. Orientation accuracy is determined by the purpose of the satellite. For a satellite with a wide bottom, the error is 5 ÷ 7, with a narrow bottom - 1 ÷ 3 degrees; in this case, the potential accuracy of orientation aids can be very high (up to fractions of arc seconds), for example, for interplanetary stations.

The high quality of command information transmission is achieved by noise-immune coding and feedback: the reception of each command is confirmed via the reverse channel of the satellite - instrumentation.

In the radio channel KIP - AES (Earth - AES), the transmission of command information is combined with on-board equipment control signals and telemetry information request signals; in the satellite-Earth radio channel, the following are combined: an information channel through which telemetric and commercial information is transmitted, a feedback channel and a reverse measurement channel. To synchronize signals in co-located radio systems, special synchronization sequences are transmitted over one of the radio channels, the form of which depends on the channel separation method used.

For channel separation, TDM with time division (TDM), frequency division (FCD), code division (CDC) and combined channel division can be used.

With QKD, each channel is assigned a time interval, as is the case with TDM, however, the signals of such channels are transmitted in any sequence in the frequency band allocated for them, due to the fact that each data block contains information and address components. QDM systems have higher noise immunity, but their bandwidth is less than with TDM or FDM.

Taking into account the multifunctionality of the SSU and K systems and the structural heterogeneity of the transmitted signals, complex types of modulation PWM - FM, KIM - FM - FM, IM - FM - FM (with time division of channels - TRC) and AM - FM , FM - FM, FM - AM (with frequency division of channels - FDM).

Since the channels of the command and control system are combined with commercial channels of a satellite communication system or with scientific information channels of satellite systems special purpose, the same frequency range is used as carriers in radio channels: from hundreds of MHz to tens of GHz.

We quickly get used to progress. Things that seemed fantastic to us a few years ago are not noticed today and are perceived as always existing. It is enough to delve into old things, when suddenly there is a monochrome mobile phone, floppy disk, tape cassette or even a reel. It was not so long ago. Not so long ago, the Internet was “on coupons” to the creak of a modem. Does anyone remember 5.25" hard drives or even tape cassettes computer games. And there will definitely be someone who will say that in his time there were 8 "floppies and bobbins for ES computers. And at that moment nothing was more modern than this.

These weeks you can watch the traditional events dedicated to the launch of the first Sputnik - the beginning of the Space Age. By chance, the satellite, which should have been the first, became the third. And the first to fly was a completely different device.
This text is about how easy it is now to hear satellites in near-Earth orbits and how it was at the beginning of the space age. To paraphrase the once famous book by E. Iceberg: “A satellite is very simple!”

Over the past 5-10 years, space has become closer to non-specialists than ever before. The advent of SDR technology and then RTL-SDR dongles opened up an easy path into the world of radio for people who never aspired to it.

Why is it necessary?

Remark about radio amateurs and the first satellites

If Sputnik was a big surprise for the West, then at least Soviet radio amateurs were warned several months before the event.
Looking at the pages of the Radio magazine, one can find articles from the summer of 1957 both on an artificial satellite, the launch of which is expected in the near future, and on the scheme of equipment for receiving satellite signals.
The excitement caused by Sputnik was unexpected, and had a strong impact on such "non-scientific" areas of society, such as fashion, car design, etc.
The Kettering Group of amateur satellite trackers became famous in 1966 when they discovered the Soviet cosmodrome at Plesetsk. A group of observers arose in the gymnasium of the city of Kettering (Great Britain) and initially the teacher, using radio signals from satellites, demonstrated the Doppler effect in physics lessons. In subsequent years, the group brought together amateurs, specialists from different countries. One of its active members is Sven Gran, who has worked all his life in the Swedish space industry (Swedish Space Corporation).

On his website, he published articles about the history of early astronautics, audio recordings made in the 1960s-1980s. It is interesting to listen to the voices of Soviet cosmonauts during everyday communication sessions. The site is recommended for study by lovers of the history of astronautics.

Curiosity. Although “everything can be found on the Internet,” few people think that from the beginning someone puts this “everything” on the Internet. Someone writes stories, someone takes interesting photos, and then it diverges over the network with retweets and reposts.

You can still listen to the conversations of the cosmonauts, who are especially active at the time of the arrival/departure of the crew from the ISS. Some people managed to catch the negotiations during the spacewalk. Not everything is shown on NASA TV, especially because over Russia for NASA these are flight blind spots, and TDRS are still not flying in sufficient numbers. Out of curiosity, you can take NOAA weather satellites (an example of a technique) and Meteor (images have a better resolution example) and find out a little more information than is published in the media.

You can find out first hand how many cubesats are doing.

Some have programs for receiving and decoding telemetry, others explicitly telegraph. Examples can be viewed.

It is possible to observe the work of launch vehicles and upper stages during the launch of cargo into a given orbit. The same equipment can be used to track stratospheric probes. Here, for example, an amazing case for me - the balloon took off from Britain on July 12 and at an altitude of 12 kilometers has already made a couple of trips around the world, flying to the North Pole. Recently seen over Siberia. There are very few receiving stations involved in the project.

Actually, what is needed for admission?

1. A receiver operating in the required range. In most cases, RTL-SDR meets sufficient requirements. Preamplifier, notch filter recommended. It is recommended to use a USB extension cable with ferrite filters - this will reduce noise from the computer and allow you to place the receiver closer to the antenna. Good result gives the shielding of the receiver.
2. Antenna for the selected range. " Best Amplifier is an antenna. Whatever preamplifier is installed after the antenna, but with a bad antenna, it will only amplify the noise, and not the useful signal.
3. In the case of receiving a satellite signal, you need to know what flies, where and when. This requires satellite tracking programs that indicate and predict the position of the satellite at a certain moment.
4. Programs for receiving and decoding cubesat telemetry or meteorological satellites.

A feature of receiving a signal from satellites is the distance and the Doppler effect.
On the theory of reception is well written in this document from page 49 -
Satellite communication Construction of a remotely operated satellite ground station for low earth orbit communication .

The derived formula shows that the power received by the receiver directly depends on the characteristics of the transmitting and receiving antennas and is inversely proportional to the square of the distance between the receiver and transmitter at the same wavelength. The longer the wavelength, the less the radiation is scattered ("Why is the sky blue?").

A satellite flying overhead is a few hundred kilometers away, while a satellite flying on your horizon may be a couple of thousand kilometers away. Which naturally reduces the level of the received signal by orders of magnitude.

And the transmitter power is not great, then the chances of successful reception are not great. For example, FunCube-1 has a transmitter power of 300 mW on the illuminated side, and only 30 mW in the shade.

What kind of antenna do you need, and for what range?

First of all, it depends on the place of reception and objects of reception. If this is a satellite with a polar orbit, then sooner or later it will fly over the receiving station. These are weather satellites, many are cubesats. If, for example, this is the ISS, and the receiving station is located in Moscow, then the ISS will only fly over the horizon. And in order to communicate or hear the satellite for a long time, it is necessary to have highly efficient antennas. Therefore, it is necessary to decide - what is affordable flies within reach from the place of reception.

What programs exist for tracking satellites, indicating and predicting the position of the satellite at a certain moment?

Online tools:
- www.satview.org
- www.n2yo.com

From programs for Windows: classic Orbitron (program review) and, for example, Gpredict.

The latter shows information on satellite frequencies. There are programs for other platforms, for example, for Android.

We will use Orbitron and frequency information from third-party sources.

How do programs calculate satellite orbits?

Fortunately, the necessary data for calculating orbits (TLE set of orbit elements for an Earth satellite) are freely distributed on the Internet and are available. You don't even have to think about it - the programs automatically download the latest data on the orbits of space objects.

But it was not always so

The North American Aerospace Defense Command (NORAD) maintains a catalog of space objects and in fact the publicly available catalog is not complete - it does not contain US military satellites. Groups of amateur enthusiasts are engaged in catching such objects. Sometimes they manage to find an object missing in the open database.

The question of determining and predicting the orbit arose even before the launch of satellites. In the USSR, a wide circle of observers and instruments was involved in solving this problem. In the observation and measurement of the Sputnik orbit, in addition to regular trajectory measurement stations, observatories and departments of higher educational institutions were involved, and the selected easily accessible radio amateur band made it possible to attract an army of radio amateurs to the observations of the first satellites - in the Radio magazine of 1957, you can find a diagram of a direction-finding installation, a tape recording with which the radio amateur had to send to the USSR Academy of Sciences. Direction finders of the Krug system, belonging to a completely different department, were involved in unusual work at the first stage.

Soon the ballistics of NII-4 achieved great success. The Strela-2 computer program developed by them for the first time made it possible to determine the orbit parameters not from direction finders, but from the results of trajectory measurements obtained by the Binocular-D stations at NIPs. It became possible to predict the movement of satellites in orbit.
The Irtysh trajectory measurement stations of the first generation were gradually replaced by the new Kama and Vistula stations with significantly higher technical indicators in terms of range, accuracy and reliability. In the 1980s, laser rangefinders appeared. You can read more details.

The stations measured the orbits not only of “their own”, but also of the satellites of their favorite potential enemy. Very quickly, optical and then radio reconnaissance satellites appeared in orbit. About what they could see back in 1965 will be below. In the meantime, I will remember an anecdotal story about soldiers in the far northern part, probably the only entertainment that was following the rules of radio and “optical” masking at the time of the passage of the corresponding satellites. Once, before the passage of an American optical reconnaissance satellite, they, naturally for fun, used the slag from the boiler room to write a huge word in the snow.

But what about those who like to hunt for satellites? They had to listen to the broadcast, peer into the sky after receiving news about the launch of a rocket from the cosmodrome. Usually a few orbits after launch were predictable.

In the photo, 2000 maps containing sets of orbit elements for Earth satellites received by Sven Gran from NASA in the period 1977-1990. Then they could be obtained via dial-up access and then, a few years later, on the Internet. Sven scanned these maps for a Facebook themed group. they contain sets of elements that are not in the Spacetrack.org database.

These data were used to predict the orbits on which observation of space objects is possible.
Naturally, no computers - only these two stencils were used 25 years ago. And by the time TLE was received, the data was not fresh.

Later, Sven used his own written PC programs to calculate the orbits.

During the flight of the Sputnik, KIK did not yet have its own computing center, and the allocated computer time on the computers of other organizations was not enough for all calculations, and the Sputnik orbit was predicted quite accurately by specially made stencils.

So, we can see satellites from an open base in the Orbitron program window, they are divided into geostationary, amateur radio, weather, ISS, etc. categories. Not all of them are of interest to reception, some do not work and are of interest only to night sky photographers.

The frequencies of working satellites can be found here:

Whatever antenna the general condition is - away from obstacles and higher from the ground. The more open the horizon, the longer the session will last. And do not forget that in the case of a directional antenna, it must be “directed” towards the satellite.

A very big note about Soviet deep-space communication antennas

The development of the R-7 family of rockets proceeded faster than the development of satellites, partly because the "go-ahead" for the satellites was given when the R-7 had already entered the stage of flight tests. The speedy creation of the third, fourth stages made it possible to reach the second cosmic velocity and carry out a rocket flight to the planets, the Moon, a flyby of the Moon with a return to the Earth and hitting the Moon. There was no time to design something from scratch, ready-made devices and components were used. For example, the antenna installation of the Zarya station for communication with the first manned spacecraft consisted of four spirals mounted on the basis of a searchlight installation left after the war.

In the conditions of time pressure for deep space communications, those antennas were used that were already in right place and the required characteristics. You can read more about the temporary space communications center.

Simultaneously with the launches towards the Moon, two capital centers for deep space communications were built "nearby" with the world's largest, at that time, space communications antennas (by the way, journalists called them Centers for deep space communications, but the real names are different - NIP-10 and NIP -16, but these, for some reason, are not quite correct names.).

The complex was also built from "ready-made units" and therefore erected in record time. The use of gun rotators as the base of the antennas caused the CIA slight confusion and for some time they believed that this was a coastal battery being built. Two years later, an oddity occurred related to the Soviet experiment at the Pluto complex to clarify the value of the astronomical unit by radar of Venus. Probably, officials in the USSR decided that the significantly refined value of the astronomical unit was a state secret and distorted the published result of the experiment. The clumsy attempt to hide the meaning was laughed at by astronomers:

we should congratulate our Russian colleagues on the discovery of a new planet. It surely wasn't Venus!

The antenna, which played a crucial role in the study of neighboring planets in the 1960s and 1970s, was cut to metal by Ukraine in November 2013.

To quote Boris Chertok:

Hidden text

According to preliminary calculations, for reliable communication with spacecraft located inside the solar system, a parabolic antenna with a diameter of about 100 meters must be built on Earth. The cycle of creating such unique structures was estimated by optimists at five to six years. And before the first launches on Mars, antenna crews had less than a year at their disposal! By that time, the parabolic antenna of the Simferopol NIP-10 was already under construction. This antenna with a diameter of 32 meters was built for future lunar programs. It was hoped that its operation would begin in 1962.

The chief designer of SKB-567, Evgeny Gubenko, accepted the bold proposal of engineer Efrem Korenberg: instead of one large paraboloid, eight sixteen-meter "cups" on a common turntable should be connected into a single structure. The production of such medium parabolic antennas was already well established. It was necessary to learn how to synchronize and add in the required phases the kilowatts emitted by each of the eight antennas during transmission. When receiving, it was necessary to add thousandths of a watt of signals reaching the Earth from distances of hundreds of millions of kilometers.

The development of metal structures for mechanisms and drives for slewing bearings was another problem that could take several years. Not devoid of a sense of humor, Agadzhanov explained that Khrushchev's ban on the construction of the newest heavy ships of the Navy provided significant assistance to cosmonautics. Ready-made turrets of the main caliber gun turrets of the battleship under construction were quickly redirected, delivered to Evpatoria and installed on concrete bases built for two antenna systems- receiving and transmitting.

Sixteen-meter parabolic antennas were manufactured by the Gorky Machine-Building Plant of the defense industry, the metal structure for their combination was mounted by the Research Institute of Heavy Engineering, the drive equipment was debugged by the Central Research Institute-173 of defense equipment, electronics of the guidance and antenna control system, using ship experience, developed MNII-1 of the shipbuilding industry, communication lines within the NIP -16 and its access to the outside world was provided by the Ministry of Communications, Krymenergo brought the power line, military builders laid concrete roads, built office premises, hotels and a military camp with all services.

The scale of the work was impressive. But the front was so wide that it was hard to believe in the reality of the terms that Agadzhanov called.

During the conversation, Gennady Guskov drove up. He was Gubenko's deputy, here he supervised the entire radio engineering department, but, if necessary, intervened in construction problems.

Both ACS-1000, receiving and transmitting, will be commissioned on time! We won't let you down," he said cheerfully.
- Why a thousand? asked Keldysh.
- Because the total effective area of ​​the antenna system is one thousand square meters.
- No need to boast, - Ryazansky intervened, - the total area you will have is no more than nine hundred!

It was a dispute between adherents of different ideas, but at that time it was not up to a hundred square meters.

After another visit to the temporary communications center in Simeiz, Korolev and Keldysh visited rapidly erected communications centers on their way to the plane. In 1960, the Pluton radio engineering complex was commissioned at NIP-16, 7 months (!) After the start of construction, becoming the most powerful in the history of mankind at that time.

Two years later, the Katun long-range space communication station was built at NIP-10 with an antenna with a diameter of 25 meters, which was soon increased to 32.

Members of the State Commission G.A. Tyulin, S.P. Korolev (since 1966 G.N. Babakin), M.V. Keldysh attached special importance to the flight of lunar and interplanetary vehicles. As a rule, after the launch of these spacecraft, they arrived at NIP-10 or NIP-16, heard reports from the leadership of the GOGU or its groups, and in case of emergency, the developers of onboard and ground technical equipment.

The potential adversary was actively interested in what was happening in the Soviet cosmonautics, thanks to which you can now learn a lot of interesting things from declassified reports and satellite photos. The topic of satellite espionage is very interesting and voluminous, those who wish can read, for example, The US Deep Space Collection Program.

Here is an example of a fragment of a satellite photo and a fragment of a diagram from a CIA report on the largest Soviet space communications center.

Without the CIA report, I would not have guessed that this was the HF antenna field of the communications center, which also carried out the observation of the first Satellites.

The CIA's awareness of some issues is amazing, and it is clear that this is analytics, and not undercover information and a high class of engineers correctly interpreting the purpose of the structures in the photo.

In the American photo, the site of the Katun deep-space communication station with control buildings and the TNA-400 antenna.
The TNA-400 antenna is inclined towards the horizon and is conducting a communication session ... In the center, on the upper border, the antenna rectangle in the form of an "antenna array" with in-phase helical emitters is a 10 kW transmitter station for communication with lunar ships. She looked like this:

Shooting date October 5, 1965. Judging by the shadows, it's before noon. A day earlier, on the morning of October 4, Luna-7 was launched.

.

The signal is not very good, a low noise amplifier is needed. The spectrogram shows that the BPSK signal is interrupted by a tone every 5 seconds.

If you managed to receive the signal, then you can proceed to the next step - decoding the signal. In the case of FUNCube, you need to download the Funcube telemetry dashboard program

Set up the program following the instructions:

And we receive telemetry:

How telemetry of Soviet spacecraft was deciphered in the first space decade

I will quote Boris Chertok and Oleg Ivanovsky.

On October 8, 1967, having covered a distance of over 300 million km, Venera-4 entered the planet's gravity zone. The final session has begun. According to the rate of increase in the frequency of the signal received from the OO, a rapid increase was felt - under the influence of the gravitational field of Venus - in the speed of meeting with the planet. But then the signal disappeared - the oncoming atmospheric flow violated the orientation of the parabolic antenna of the station to the Earth. At the same moment, the on-board automatics issued a command to separate the SA. There was silence in the small hall of the Evpatoria flight control center: everyone froze in anticipation of a signal. Excruciatingly slow Digital Watch counted the seconds. Finally on speakerphone heard a joyful cry: “There is a signal from the SA!” A few minutes later, information began to arrive: “Pressure 0.05 atm, temperature minus 33 ° C, CO2 content in the atmosphere about 90%” - and after a short pause: “Information from the radio altimeter is out of order”.
This is our specialist Revmira Pryadchenko, looking at an endless tape with binary symbols flying across the table, visually - not only personal computers, but even simple electronic calculators did not exist then - she singled out the desired channel, turned the binary symbols into a number and accurately reported the value of the parameter.

***

One of Sergei Leonidovich's assistants leaned slightly towards the indicator screen:
- There is telemetry. The first switch should go.
- Mirochka in place? Babakin asked.
- Of course. Now let's ask what she sees.
... Mirochka. Or, if completely, - Revmira Pryadchenko.
Her parents came up with such a name, combining two words in it: “revolution” and “peace”. There was such a fashion in the past years. In the group of managers, Mira was an exceptional person, who had a phenomenal ability to remember dozens of operations that were supposed to be performed by the instruments and systems of the station according to radio commands given from the Earth or from onboard PES. Perhaps, like no other, she immediately knew how to understand and decipher telemetry signals, sometimes quite confused by the cosmic dissonance of radio interference.
By God, this gift of hers could successfully compete with any automatically information processing. More than once, our managers have perplexed sophisticated colleagues, declaring that where information from VENER is being processed by the special Mira-1 system.
- How is it - "Mira-1" ?! There are no such machines. Computer "Mir-1" is, and "Mira-1" ...
- That's just it, that you have "Mir", and we have "Mira"!
And what beautiful poems Mirochka wrote ...
Babakin took the microphone.
- Mirochka! Good afternoon. Well, what do you have?
- Hello, Georgy Nikolaevich! She recognized the Chief by his voice. - While I can not say anything. Telemetry is a complete failure. Options cannot be selected.
Well, at least something...
- Now ... wait a minute ... so far I can only say one thing, but I can’t guarantee ... here ... DPR is not normal ...
The chief lowered his hand with the microphone.
- DPR ... DPR ... Is this pressure after the reducer?
They moved around the table. At the same time, some confusion and concern appeared on the faces of the managers.
The big one looked first at the Chief, then at Azarch. Technical guidance exists to make decisions about what to do next in a difficult environment, whether to continue the session or give a shutdown command?
The difficulty was that a program-time device was operating on board the station, impartially issuing command-signals in the required sequence to orient the station and turn on the corrective engine. This device worked, and he did not know that some kind of DPR was not normal ...
“What can this lead to… what… what?” - the Chief thought for a second, - to increased gas consumption, to excessive thrust on the orientation nozzles, right? The station can not orient?
- Georgy Nikolaevich, we need to figure it out, - one of the managers said without hiding his excitement.
The chief took the microphone:
- Mirochka, what's up?
And the neon numbers of the stopwatch clicked off the seconds and minutes, which had become somehow very short.
- I understand, the failures are continuous, until I say anything new ...
- Turn off the station, hang up? - Big inquiringly looked at the Chief.
- Put off the retreat. Do not worry. Let the session go.
A rough, shaggy bump of the distant voice of the station beat on the indicator. Well, why, as if according to the law of "dirty things", just when the information was needed more than ever, it could not be "fished out" from the turbidity of failures and interference?
- Can we do it again? Is there enough gas in the orientation system? - The technical manager continued the interrogation. - No, you need to collect working group and carefully put everything on the shelves, in order ...
- Yes, what "shelves!" In extreme cases, the correction session will have to be repeated ...
- Is it real? Enough gas? This requires careful thought. Georgy Nikolaevich ...
The loudspeaker of the circular clicked and Mirochka's joyful voice, unusually filled with ringing notes and interrupted by excitement:
- George Nikolaevich! Deciphered! Everything is fine! DPR is OK! Fine!
And immediately the tension was gone. And on the clock - 11 hours 03 minutes. And it only took 5 minutes. Just five minutes...

According to the memoirs, the death of Soyuz-11 is connected with this, the pressure drop in which was immediately recorded on the recorder tapes, but they did not have such a talent to decipher on the fly, raise the alarm and warn the crew before they themselves felt the fatal pressure drop . Unfortunately development automatic system receiving and decrypting telemetry has not yet been completed.

When receiving a satellite signal, a phenomenon such as the Doppler effect is inevitable. On the spectrogram, it will look like this:

As the satellite approaches the receiving point, the frequency increases and decreases as it moves away. Such "drawings" on the spectrogram allow you to accurately determine that the signal belongs to a moving satellite, and not to a ground-based source of interference. When receiving telemetry, you must manually adjust the frequency of the signal. It is possible to automatically adjust the frequency and again the Orbitron program will help with this, calculating required frequency and driving the SDRSharp or HDSDR program.

Setting up HDSDR is much easier. In Orbitron, similarly to the article, install the MyDDE driver:

In HDSDR - Options\DDE client.

Before use, we synchronize the clock over the Internet (with the nearest NTP server). Have a good hunting.

Doppler effect 50 years ago

I will quote another memoir:

The remote control glows with multi-colored lights - blue and green pulses run through on the screens of oscilloscopes.
- Tick-tock, tick-tock, like a metronome, some device clicks. Time goes by slowly. Expectation. Concerned faces.
Tick-tock, tick-tock. For a long, long time the signal goes on. After all, he has to run 78 million kilometers. 4 minutes 20 seconds will be spent on this ... Yes! There is!
***
The physical Doppler effect comes to the rescue. As you know, the greater the speed of the apparatus emitting radio signals, the stronger the frequency shift of this signal. The magnitude of the displacement can determine the speed and stability of the flight.
It's already seven in the morning. It's light outside the window. The counters of the frequency tuning system, which constantly reconfigures the parameters of the receiving antenna so as to monitor the change in the signal that occurs due to the increase in speed, begin to part, which means that the attraction of Venus is becoming stronger. The speed is increasing. The planet is only 15 thousand kilometers away.
The buzzer almost chokes. The speed is growing rapidly. Venus is getting closer and closer. At 07:25 the last command of the Earth left - to turn on the time-program device. The station is now completely independent.

What is this frequency tuning system? You can imagine this system and its complexity and size, if you know that it consisted of many quartz resonators differing from each other in frequency of ONE HERTZ.