RU2783202C2 - Repeater satellite - Google Patents

Abstract

FIELD: communication.

SUBSTANCE: invention relates to repeater satellites. The repeater satellite includes a unit for determination of mutual angular velocities of satellites, connected between the second output of a unit for formation of service messages, outputs of a unit of bearing signal analyzers, and the second and the third inputs of a unit for control and selection of modulators, an angular velocity recorder connected between outputs of the unit for determination of mutual angular velocities of satellites and inputs of the unit for control and selection of modulators, while a case of the repeater satellite is made in the form of a hyperboloid, and optical antennas in a unit of optical intersatellite transmitting antennas are located in a crown shape along a perimeter of the case of the repeater satellite.

EFFECT: increase in the reliability of communication between repeater satellites in an area of intersection of their orbits.

1 cl, 12 dwg

Description

The invention relates to the relaying of information, in particular to relay satellites.

Known relay satellites included in the low-orbit satellite communication network One Web [see. site https://www.oneweb.world/], which includes a system of satellites in circular orbits of the earth. The disadvantage of this device is the lack of an inter-satellite path, the lack of adaptive switching on board, as well as on-board data processing, including information reading, analysis, reformatting and sending, which slows down or complicates the delivery of data to the recipient.

Known relay satellites included in the low-orbit satellite communications network Starlink [see. site https://www.starlink.com/] including the formation of satellites in circular orbits of the earth. The disadvantage of this device is the lack of an inter-satellite path, the lack of adaptive switching on board, as well as on-board data processing, including information reading, analysis, reformatting and sending, which slows down or complicates the delivery of data to the recipient.

An analogue of a repeater satellite is a well-known repeater satellite [RF patent No. 2376212, IPC B64G 1/00, IPC B64G 1/22, priority dated 05/19/2008, registered in the State Register of Inventions of the Russian Federation on 12/20/2009], containing antennas and an onboard complex case frame in the form of a parallelepiped, with side, top and bottom panels installed on it. Inside the platform structure, the frame space is divided by an intermediate panel into a service systems compartment and a payload compartment.

The disadvantage of this relay satellite is the insufficient reliability of maintaining communication between the satellites in the area of the intersection of their orbits, due to the fact that the frame of the body in the form of a parallelepiped obscures the visibility zones of the antennas located on it, which, at a high angular velocity of the mutual movement of the satellites, makes it difficult to keep the optical beam of the transmitting antennas of the first satellite on the second satellite and reduces the reliability of the connection.

The closest in technical essence and the achieved positive effect - the prototype is a relay satellite [see. patent of the Russian Federation No. 2622304, B64G 1/10, priority dated 11/17/2015, registered in the state register of inventions of the Russian Federation on 05/22/2017], containing a housing in the form of a shell of rotation made of composite material of a hollow cylindrical shape, having a mesh structure formed by crossing the ribs with each other, while reinforcing elements are fixed at the ends of the mesh shell.

The disadvantage of this relay satellite is the insufficient reliability of maintaining communication between the satellites in the area of the intersection of their orbits, due to the fact that the shell of rotation of a cylindrical shape obscures the visibility zones of the antennas located on it, which, at a high angular velocity of the mutual movement of the satellites, makes it difficult to keep the optical beam of the transmitting antenna the first satellite on the second satellite and reduces the reliability of the connection.

Known on-board complex satellite relay "Aksai" [see. patent of the Russian Federation No. 2097926, Η04В 7/185, priority dated 19.04.94, bull. No. 33 dated 11/27/97], designed to operate in a multi-satellite communication system in which neighboring satellites can exchange subscriber and service information, including a series-connected block from to receiving antennas, a receiver block, a transmitter block and a block from to transmitting antennas, a switching block , a navigation block, a service signal extraction unit, a service signal generation unit and a blocking signal generator, wherein the switching unit is connected between the outputs of the transmitter unit, the service signal extraction unit is connected between the outputs of the receiver unit and the first inputs of the service signal generation unit, the navigation unit, the service signal extraction unit signals, the service signal generation unit and the blocking signal generator are connected in series and the outputs of the last of them are connected to the third inputs of the switching unit, the second inputs of which are connected to the outputs of the navigation unit, and the outputs of the service signal generation unit connected to the second inputs of the transmitter unit.

The disadvantage of this device is the lack of reliability of maintaining communication between satellites in the area of intersection of their orbits, due to the fact that the high angular velocity of the mutual movement of the satellites makes it difficult to keep the beam of the transmitting antenna on the neighboring satellite and reduces the reliability of communication.

The closest in technical essence and achieved positive effect for the relay satellite - the prototype is the relay satellite [see. patent of the Russian Federation No. 2673060, Η04V 7/185, priority dated 11/20/17, registered in the state register of inventions of the Russian Federation on 11/22/18], intended for operation in a multi-satellite communication system in which neighboring satellites can exchange subscriber and service information, including a switching unit, a unit receiving subscriber radio antennas and a block of subscriber radio receivers, a block of receiving optical inter-satellite antennas and a block of optical inter-satellite receivers, a solar sensor and an orientation block connected in series, a navigation block, a block for generating service messages and a blocking signal generator, a block for separating service signals connected in series, a block for extracting bearing signals , a block of bearing signal analyzers and a block of control and selection of modulators, a block of inter-satellite optical transmitters, a block of subscriber radio transmitters, blocks of transmitting inter-satellite optical antennas and subscriber radio antennas

The disadvantage of this device, adopted as a prototype, is the lack of reliability of maintaining communication between satellites in the area where their orbits intersect, due to the fact that the high angular velocity of the mutual movement of the satellites makes it difficult to keep the optical beam of the transmitting antenna on the neighboring satellite and reduces the reliability of communication.

The technical result of the claimed invention is to increase the reliability of communication between satellites in the area where their orbits intersect.

The technical result is achieved by the fact that in a repeater satellite containing a block of transmitting and a block of receiving optical inter-satellite antennas, a block of receiving subscriber antennas placed on the body of the repeater satellite, as well as a series-connected block of subscriber receivers, a switching block, a block of subscriber transmitters and a block of transmitting subscriber antennas, a block of inter-satellite receivers, a block for separating service signals, a block for extracting a bearing signal, a block for bearing signal analyzers, a block for controlling and selecting modulators, a block for generating service messages, and a blocking signal generator connected to the second inputs of the switching block, to the third inputs of which the outputs of the block for generating service messages are connected, the second outputs of the switching block are connected through the block of inter-satellite transmitters and the block of modulators to the inputs of the block of transmitting inter-satellite antennas, the inputs of the block of modulators are connected to the output of the block control and selection of modulators, the navigation unit, the outputs of which are connected to the fourth inputs of the switching unit, the second inputs of the block for generating service messages and the first inputs of the orientation unit, to the second inputs of which the output of the sun sensor is connected, connected to the second input of the control and selection of modulators, which, in turn, it is connected to the block for generating service messages, characterized in that it contains a block for determining the mutual angular velocities of the satellites, connected between the second output of the block for generating service messages, the outputs of the block of bearing signal analyzers and the second and third inputs of the control block and selection of modulators, the register of angular velocities connected between the outputs of the unit for determining the mutual angular velocities of the satellites and the inputs of the control unit and selection of modulators, while the body of the relay satellite is made in the form of a hyperboloid, in the block of optical inter-satellite transmitting antennas, optical antennas are located are laid crown-like along the perimeter of the satellite body.

The essence of the invention is illustrated by graphic materials, where:

In FIG. 1 shows the intersection of the orbits of two repeaters in isometric projection;

in fig. 2 shows the intersection of the orbits of two repeaters in the Mercator projection;

in fig. 3 shows a scan of the beam section of the radiation pattern of the transmitting antenna of the optical range used in the inter-satellite path;

in fig. 4 shows the interaction of the transmitting antennas of the optical range of the repeater satellite with the neighboring satellite. Due to the complexity of the drawing, the body of the repeater satellite is depicted as a polyhedron instead of a hyperboloid;

in fig. 5 shows a schematic view of the design of the block of transmitting antennas;

in fig. 6 shows a schematic view of the design of the body of the repeater satellite, in the form of a hyperboloid, optimized for placement of blocks of transmitting and receiving antennas;

in fig. 7 is a block diagram of a satellite transponder as a whole;

in fig. 8 shows a block diagram of the control unit and selection of modulators;

in fig. 9 shows a block diagram of the block for determining the mutual angular velocities of the satellites;

in fig. 10 shows a block diagram of the control signal generation unit;

in fig. 11 is a schematic view of the transponder receiving antenna;

in fig. 12 shows the formats of the subscriber and service messages.

Designations on the figures:

In FIG. one

1 - the first relay satellite (CP ₁ ) in orbit;

2 - second relay satellite (SR ₂ ) in orbit;

3 - orbit SR ₁ ;

4 - orbit SR ₂ ;

5a - the direction of communication CP ₁ - CP ₂ to the pole of intersection of their orbits;

5b - the direction of communication CP ₁ - СР ₂ after the pole of intersection of their orbits;

6 - axis of intersection of orbits CP ₁ - CP ₂ ;

- вектор скорости СРь

- velocity vector Cp

- вектор скорости СР₂.

- velocity vector СР ₂ .

In FIG. 2

1 - CP ₁ in orbit;

2 - SR ₂ in orbit;

3 - orbit SR ₁ ;

4 - orbit SR ₂ ;

5a - the direction of communication CP ₁ - CP ₂ to the pole of intersection of their orbits;

5b - the direction of communication CP ₁ - СР ₂ after the pole of intersection of their orbits;

6 - axis of intersection of orbits CP ₁ - СР ₂ .

In FIG. 3

aa is the position of the beam formed at the first time of the scan cycle;

mn is the position of the beam formed at the final moment of the scan cycle.

In FIG. four

7 - antenna block receiving optical inter-satellite antennas;

8 - antenna of the block of receiving subscriber antennas of the radio range;

9 - block transmitting optical inter-satellite antennas;

10 - scanning area of the first transmitting optical inter-satellite antenna;

11a - the first scanning area of the second transmitting inter-satellite antenna;

11b - second scanning area of the second transmitting optical inter-satellite antenna;

12a - the first scanning area of the third transmitting optical inter-satellite antenna;

12b - the second scanning zone of the third transmitting intersatellite antenna of the satellite;

13 - solar sensor

- вектор скорости СР₂.

- velocity vector СР ₂ .

In FIG. 5

9 - block transmitting optical inter-satellite antennas.

In FIG. 6

- высота корпуса, выполненного в форме однополостного гиперболоида;

- the height of the body, made in the form of a single-sheeted hyperboloid;

r - radius of the upper opening of the body;

R is the radius of the lower body opening;

L - body stringer length;

ϕ - angle of inclination of the body stringer.

In FIG. 7

7 - antenna block receiving optical inter-satellite antennas;

8 - antenna of the block of receiving subscriber antennas of the radio range;

9 - block transmitting optical inter-satellite antennas;

13 - solar sensor;

14 - block of inter-satellite receivers;

15 - block of subscriber receivers;

16 - switching unit;

17 - block selection of service signals;

18 - navigation block;

19 - unit for generating service messages;

20 - blocking signal generator;

21 - block for extracting the bearing signal;

22 - bearing signal analyzer unit;

23 - block for determining the mutual angular velocities of the satellites (BOVUS-S);

24 - control unit and selection of modulators;

25 - block of modulators;

26 - block of inter-satellite transmitters;

27 - block of subscriber transmitters;

28 - block transmitting subscriber antennas;

29 - block orientation;

40 - register of angular velocity.

In FIG. eight

23 - block for determining the mutual angular velocities of the satellites;

44 - control signal generation unit;

30 - block allocation of the correction code pointing;

31 - correction code generation unit;

32 - register block.

In FIG. 9

33 - block of local clocking;

34 - block delay;

35 - register block;

36 - block generating a difference code;

37 - block for calculating the sign of the angular velocity;

38 - block for calculating the module of angular velocity.

In FIG. ten

39 - solar sensor register;

40 - register of angular velocity;

41 - bearing signal register;

42 - code register pointing correction;

43 - control code generator.

In FIG. eleven

7a - 7f photo detectors of the receiving optical inter-satellite antenna;

In FIG. 12

a) - a message addressed to the subscriber - the recipient;

b) - service message of the inter-satellite path;

GF - head flag;

FG - group flag;

FS - segment flag;

ZF - final flag;

X _R , Y _R , N _R - geographic coordinates and personal number of the recipient subscriber;

X _i , Y _i - geographical coordinates of the satellite - the repeater that sent this service message;

NOGKSR - code of the serial number of the satellite - the repeater that sent this service message;

KOH - service message trailer.

The repeater satellite works as follows.

Moving in orbit, relay satellites 1 and 2 (see Fig. 1) receive messages from terrestrial subscribers and from neighboring repeaters, process the received message headers in the onboard switch and send messages either in the direction of terrestrial subscribers or in the direction of a neighboring repeater. The number of relay satellites is not limited. An example of the interaction of two satellites is considered.

The orbits of the relay satellites 1 and 2 intersect in two areas (see Fig. 2) - in the region of the ascending node or in the region of the descending node. At the same time, in the areas of intersections, the orbits of the satellites are separated from each other in height, so that the satellites do not collide. The axis of intersection of the orbits passes through the ascending or descending node and the center of the Earth.

направлены по касательной к траекториям орбит 3 и 4, а угловая скорость направления связи 5а и 56 спутников 1 и 2 изменяется по знаку и по модулю (абсолютному значению) в связи со сближением спутников 1 и 2 в районе полюса 6 с последующим расхождением спутников (см. фиг. 2). Угловая скорость взаимного перемещения двух спутников 2 и 4 перед сменой знака нарастает, а после смены знака - убывает.When crossing (see Fig. 1) orbits 3 and 4 of two relay satellites 1 and 2, the direction of communication of satellite 1 to satellite 2 in the region of the pole of the axis of intersection of orbits 6 changes to the opposite - from 5a to 56. In this case, the velocity vector

are directed tangentially to the trajectories of orbits 3 and 4, and the angular velocity of the communication direction 5a and 56 of satellites 1 and 2 changes in sign and in absolute value (absolute value) due to the approach of satellites 1 and 2 in the region of pole 6 with the subsequent divergence of the satellites (see Fig. 2). The angular velocity of the mutual movement of the two satellites 2 and 4 before the change of sign increases, and after the change of sign - decreases.

For inter-satellite communication, that is, to detect, hold and track the second satellite 2, the transmitting antenna of the block 9 of the first satellite 1 scans the beam from position aa to position mn (see Fig. 4). Each position has its own code signal.

To ensure the continuity of inter-satellite communication, the scanning areas "aa-mn" of the transmitting antennas of unit 9 (see Fig. 4) of the first satellite 1 are switched from the scanning area 10a of one antenna of the unit 9 to the scanning area of the other antenna of the unit 9. In this case, the scanning area 10a is overlapped by scan area 11a and scan area 12a, and the latter two overlap each other and are overlapped by zones 116 and 126. Other options for transferring communication from one scan area to another are possible. For the second satellite 2, in this case, continuity of communication with the first satellite 1 is ensured, regardless of the velocity values and the sign of the change in its angular velocity relative to the first satellite 1.

Initially, after launching into orbit, each satellite (first 1 or second 2) is oriented towards the sun by the solar sensor 13 (see Fig. 4) (rough guidance is carried out), and continues to fly on the sunny side of the Earth, all the time focusing on the sun. When moving into the shadow of the Earth, each satellite continues to orient itself according to the data of the onboard equipment until it returns to the illuminated side.

R, r и ϕ.On the second satellite 2, the receiving antenna takes the direction of the beam received from the first satellite 1 using photodetectors 7a - 7e (see Fig. 11), after which the second satellite 2 generates a bearing response signal from the information from the outputs of the photodetectors and sends it in the direction of the first satellite 1 through one of the antennas of the block 9, which is structurally made on each satellite (the first 1 or the second 2) in the form of a crown (see Fig. 5). Block 9 is placed on the lower and upper housing openings of each satellite (see Fig. 6). The body of each satellite for placing the antennas of block 9 is structurally made in the form of a hyperboloid (see Fig. 6), which provides a minimum weight, dimensions and the simplest manufacturing technology. The main geometric characteristics of such a housing are indicated in Fig. 6 as L,

R, r and ϕ.

The interaction of the first and second satellites 1 and 2 when sending user messages and when establishing and maintaining communication in inter-satellite paths is carried out as follows (see Fig. 7).

Launched into orbit, each satellite on the solar sensor 13 (see Fig. 4) is oriented by the orientation block 29 (see Fig. 7) to the sun (rough guidance is carried out), and continues to fly on the sunny side of the Earth, continuing to be oriented towards the sun. When moving into the shade, the orientation unit 29 works out the position of the satellite according to the signals of the navigation unit 18 until it returns to the illuminated side of the Earth. In this case, the scanning areas of the inter-satellite beams 10a, 11a, 11b, 12a, 12b and others (see Fig. 4) of the first satellite 1 are oriented towards the second satellite 2.

The signal from the subscriber on the first satellite 1 is received by the antenna of block 8 (see Fig. 7) and is switched by the switching unit 16 to the transmitting subscriber antenna of block 28 and further to the subscriber, or to the transmitting inter-satellite antenna of block 9, which formed the beam 10a, or 11a, or 11b, or 12a, or 12b or another, to the second satellite 2 at the signal of the modulator block 25.

After receiving from the first satellite 1 a subscriber message by the inter-satellite antenna block 7 of the second satellite 2, it arrives at the block of inter-satellite receivers 14, then to the switching block and, further, either to the block of inter-satellite transmitters 26, or to the block of subscriber transmitters 27. After block 27, the message through a block of transmitting subscriber antennas 28 is sent in the direction to the receiving subscriber. After block 26, the message is sent through the block of modulators 25 and block 9 in the direction of the next satellite on the way to the subscriber, which in FIG. 1 and FIG. 2 is not shown so as not to overload the image. The interaction algorithm of the second satellite 2 with the next satellite, in this case, is identical to the interaction of the first and second satellites, but the second satellite 2 performs the functions of the first satellite 1, that is, sends a message to the next satellite, and the next satellite receives this message.

The operation of the switching unit 16 when the relative position of the first satellite 1, subscribers and the second satellite 2 changes is corrected by the signals of the navigation unit 18, and the blocking signal generator 20. Through the switching unit in the direction of the second satellite 2, the corresponding service messages about the bearing generated in the formation of service messages 19 are sent the second satellite 2 and the own health of the satellite 1.

The establishment and maintenance of communication continuity in inter-satellite paths is carried out as follows (see Fig. 7). In the first satellite 1, the relative angular velocity of the second satellite 2 is measured by determining the magnitude and sign of the Doppler frequency shift of the signal received from satellite 2, and the service message (response) of the second satellite 2 is analyzed about which photo detector 7a - 7e (see Fig. 11) the second satellite 2 received a signal from the first satellite 1. The magnitude and sign of the Doppler shift of the signal from satellite 2 are determined on satellite 1 in the block for determining the mutual angular velocities of satellites 23. The data on the receiving photodetector of satellite 2 on satellite 1 are determined in the block of bearing signal analyzers 22 Based on this information in the first satellite 1, the control and selection unit of modulators 24 and the unit of modulators 25 select the required antenna from block 9 and set the position of its beam for communication with the second satellite 2. That is, the choice of antenna from block 9 is carried out in accordance with values of the modulus and sign of the Doppler shift of the signal frequency, and in accordance with the data on receiving photodetector from the satellite 2.

The service message from the second satellite 2 through the blocks 7 and 14 of the first satellite 1 is fed to the signal extraction unit 17, then through the bearing signal extraction unit 21 and the bearing signal analyzer unit 22 is fed to the unit for determining the mutual angular velocities of the satellites 23 and to the control unit and selection of modulators 24. Based on the signals received from the solar sensor and blocks 22 and 23, the control and selection of modulators 24 generates a control code for the block of modulators 25, and block 25 selects the desired transmitting antenna of block 9 and sets the position of its beam.

The formation of service messages in satellites 1 and 2 is carried out in the block for the formation of service messages 19 according to signals from the navigation block 18 and the control unit and selection of modulators 24. The generated service message through the switching block 16, the block of inter-satellite transmitters 26, the block of modulators 25 enters the antenna of the block 9 and is sent in the direction of the second satellite 2.

The control unit and selection of modulators 24 (see Fig. 8) operates as follows. The guidance correction code extraction unit 30 extracts the corresponding code from the signal coming from the service signal extraction unit 17, after which the selected code is fed to the first input of the control signal generation unit 44. From the unit for determining the mutual angular velocities of the satellites 23 through the angular velocity register 40, and from bearing signal analyzer unit 22, the corresponding inputs of the control signal generation unit 44 receive the codes of the sign and module of the angular velocity, as well as the codes of the bearing signal. As a result, block 44 generates a control code for the modulator block 25. This control code enters the correction code generation block 31, from where the correction code enters the register block 32 to be written to the corresponding field of the service message. In block 32, according to the clock signals from the block for generating service messages 19 (see Fig. 7), the code of the service signal from block 17 and block 31 is written to the corresponding registers, after which, also, according to the clock signals of block 19, the generated sequence from block 32 rewritten in block 19 to generate a service message.

The unit for determining the mutual angular velocities of the satellites 23 (see Fig. 9) operates as follows. Block 23 in the first satellite 1 calculates the angular velocity of movement relative to the second satellite 2, which increases in absolute value before crossing their orbits, and then decreases. Block 23 also calculates the sign of the direction of communication to the neighboring satellite 2, which changes after the satellites pass the axis of intersection of their orbits 6. For this purpose, the code from the block of bearing signal analyzers 22 is input to the delay block 34 and, with a delay of a given number of cycles, is rewritten into a register block 35. Timing is carried out according to signals from the block for generating service messages 19, which are distributed among the component parts of block 34 by local timing block 33. The values of the code of block 22 and the code from block 35 are processed by the block for generating a difference code 36, after which the processing results are sent to the calculation block the sign of the angular velocity 37 and into the block for calculating the module of the angular velocity 38. The codes of the sign and the module of the angular velocity generated by them from the outputs of the block 34 are fed to the corresponding inputs of the block for generating the control signal 44.

The control signal generation unit 44 (see Fig. 10) operates as follows. The codes of the sign and module of the angular velocity come from the angular velocity register (RS) 40 to the input of the control code generator 43. The signal from the solar sensor 8 through the solar sensor register (SD register) 39, the bearing signal from the bearing signal analyzer unit 22 through the bearing signal register ( SP register) 41 and the guidance correction code from the guidance correction code extractor 30 through the guidance correction code register (CTC register) 42 are also fed to the corresponding inputs of the control code generator 43. Register codes 39, 40, 41 and 42 in the control code generator 43 are converted into a control code, which from the output of the shaper 43 is sent further to the inputs of the modulator block 25 and the correction code generation block 31.

Antenna block intersatellite antennas 7 (see Fig. 7) operates as follows. The beam signal from the transmitting antenna 9 is received by one of the photocells 7a - 7e (see Fig. 11). The photocell produces a signal in proportion to the beam energy falling on it. From the output corresponding to the photocell, the signal goes further to the block of inter-satellite receivers 14 (see Fig. 7) and, through blocks 17 (where the signals of the photocells of the antenna of block 7 are converted into a digital code), 21 (where the bearing code is formed) and 24 (where in addition to the bearing code, the number of the receiving antenna of block 7 is indicated) enters block 19, where the bearing code corresponding to the photocell with the best signal reception is recorded in the service message.

The message addressed to the recipient (see Fig. 12a) is processed as follows. The head flag FG designates for blocks of allocation of service signals 17 and the switch 16 the beginning of the packet of the message, the flag of the group for the service and subscriber messages are different, and the block 17 does not further process the subscriber message. Further, in the switching unit 16, the subscriber's message passes from the subscriber's input, through a number of switching elements, in each of which the head bit determines the output where the message will be sent. In this case, the head bit of the sequence is not regenerated. Thus, at the corresponding output of the switching unit, the message appears only with the SF and the number of the recipient of the message N _R . This message is broadcast by the first satellite 1 or the second satellite 2 to the sub-satellite zone, where the subscriber recognizes the SF and his number and receives the message. If you want to forward a message over the network through several satellites (more than 2), then the message header will contain several groups of codes - from "FG" to "FS before ZF". The number of such groups corresponds to the number of relays on the way to the recipient. That is, the recipient will receive only the SF, N _R and the message with KOH.

The service message (see Fig. 12b) includes one group from the GF to the FS after Y _i , since it is not intended for retransmission, but only for a neighboring satellite. The message contains information about the current sub-satellite zone of the Earth, over which satellite 1 is located, information about the health of satellite 1 and the beam pointing correction code for satellite 2. The service message in satellite 2 does not go to the subscriber input of switch 16, but passes through block 17, after which provides in it the correction of the operation of the switch 16 and the block of modulators 25. In turn, in the satellite 2 a similar message is generated for the satellite 1, to correct the blocks 16 and 25 of the latter.

Literature

1. Site https://www.oneweb.world/.

2. Website https://www.starlink.com/.

3. RF patent No. 2097926, IPC: Η04В 7/185, priority dated 04/19/94.

4. RF patent No. 2673060, IPC: Η04V 7/185, priority dated 11/20/17.

5. RF patent No. 2376212, IPC: B64G 1/00, 1/22, priority dated 05/19/2008.

6. RF patent No. 2622304, IPC: B64G 1/10, priority dated 11/17/2015.

Claims (1)

A repeater satellite containing a block of transmitting and a block of receiving optical inter-satellite antennas, a block of receiving subscriber antennas placed on the body of the relay satellite, as well as a series-connected block of subscriber receivers, a switching block, a block of subscriber transmitters and a block of transmitting subscriber antennas, a block of inter-satellite antennas connected in series receivers, a service signal extraction unit, a bearing signal extraction unit, a bearing signal analyzer unit, a control and modulator selection unit, a service message generating unit, and a blocking signal generator connected to the second inputs of the switching unit, to the third inputs of which the outputs of the service message generating unit are connected , the second outputs of the switching unit through the block of inter-satellite transmitters and the block of modulators are connected to the inputs of the block of transmitting inter-satellite antennas, the inputs of the block of modulators are connected to the output of the control unit and selection of modulators, navigation th block, the outputs of which are connected to the fourth inputs of the switching block, the second inputs of the block for generating service messages and the first inputs of the orientation block, to the second inputs of which the output of the sun sensor is connected, connected to the second input of the control unit and selection of modulators, which, in turn, is connected with a block for generating service messages, characterized in that it includes a block for determining the mutual angular velocities of the satellites, connected between the second output of the block for generating service messages, the outputs of the block of bearing signal analyzers and the second and third inputs of the control unit and selection of modulators, the register of angular velocities included between the outputs of the unit for determining the mutual angular velocities of the satellites and the inputs of the control unit and the selection of modulators, while the body of the relay satellite is made in the form of a hyperboloid, in the block of optical inter-satellite transmitting antennas, the optical antennas are arranged crown-shaped along the perimeter of the satellite body nick repeater.

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