RU2368077C1 - Method for transmission of information - Google Patents

Abstract

FIELD: physics, radio engineering.

SUBSTANCE: invention is related to communication systems and is designed for retransmission of radio-television signals. Substance of invention consists in the fact that method for transfer of information includes aiming of retransmitter receiving antenna at signal source by means of receiving antenna rotation by tilt angle and azimuth, with its further accurate aiming at signal source, and also aiming of transmitting antenna of retransmitter to subscriber station in compliance with calculated azimuth and tilt angle. Prior to rotation of receiving antenna by tilt angle to signal source, scaling mode is realised, in which receiving antenna is turned by tilt angle at calculated angle, and its position is fixed, besides rotation is carried out in the mode of the second speed, which is 4-10 times less than the first mode speed. In computer device calculated angle is compared with actual angle value measured with the help of tilt-angle scale of receiving antenna, correction for angular speed is identified. Indication devices display calculated tilt angles of signal source and subscriber station. Receiving antenna is turned to signal source by tilt angle in the first speed mode, if value of program angle is more than calculated threshold value. One or more corrections of receiving antenna position are carried out, to take tilt angle to calculated value and to fix this position of receiving antenna. Mode of receiving antenna rotation scaling is carried out by azimuth similar to scaling mode by tilt angle. Receiving antenna is turned by azimuth in mode of the first speed, maximum value of signal emitted by signal source is measured. In specified angle after passing though maximum value of signal, receiving antenna is stopped, and receiving antenna is turned in mode of the second speed in reverse direction with stop whenever signal increases up to threshold value, which makes from 30 to 70 percent from maximum value. Value of azimuth measured with the help of receiving antenna azimuthal scale is introduced into computer device. Receiving antenna is rotated in the mode of the second speed in the same direction with stop via specified angle with passing of signal maximum value and the second threshold value, which is equal to the first one. In mode of the second speed receiving antenna is rotated in reverse direction with stop, when signal increases up to the second threshold value. Value of measured azimuth is introduced in computer device, using two found values of azimuth, source of signal azimuth is defined. One or two corrections of receiving antenna position are carried out, to bring the azimuth to found value. Mode of transmitting antenna rotation scaling is realised by tilt angle, as well as rotation of transmitting antenna to subscriber station by tilt angle, one or two corrections of transmitting antenna position to bring tilt angle to calculated value and fixation of this position. Mode of transmitting antenna rotation scaling is carried out by azimuth, as well as rotation of transmitting antenna to subscriber station by azimuth, one or two corrections of transmitting antenna rotation ti bring azimuth to calculated value and fixation of this position.

EFFECT: simplified equipment of retransmitter, reduction of its mass and dimensions, lower power consumption.

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Description

The invention relates to communication systems and can be used to expand the service area in areas where, due to the terrain, there is no or unstable reception of a microwave television signal. In this case, the direct passage of the signal is hindered by the presence of a hill or a mountain barrier, as well as the fact that the receiving station may be located in a hollow. In such cases, special microwave communication lines and repeaters are used. The source of the radio television signal may be a ground source or a spacecraft (SC).

Known methods of transmitting information implemented by satellite communication stations, in particular, in the Orbit station, designed to receive television (Pokras AM, Somov AM, GG Tsurikov. Antennas for satellite communications earth stations. - M .: Radio and communications, 1985 , p.22-27). Antenna guidance on the spacecraft in these stations is carried out by servo-electric drives in automatic auto tracking, control from a software device or semi-automatic control. The station uses a parabolic reflector antenna located in a biaxial azimuth-elevation support-rotary device.

The disadvantages of this method of transmitting information are significant weight and size characteristics and power consumption, as well as the relatively high cost of the station. This is due to the technical characteristics of the station, especially the high speed of information reception and high accuracy of antenna pointing.

Terrestrial satellite communication stations are known, which are usually transceiver radios with one common parabolic antenna (for reception and transmission) (Bartenev V.A., Bolotov G.V., Bykov V.L. et al. Edited by Kantor L. A. Satellite communications and broadcasting. - M .: Radio and communications, 1997, p. 404-409). At these stations, information transfer methods are used, in which the program guidance mode is performed at a given point in space, the signal search and capture mode, as well as the exact guidance mode on the received signal (auto tracking mode). In the accurate guidance mode, various guidance methods for the received signal can be used: extreme guidance method, monopulse method, etc.

The disadvantages of these methods are: a relatively large power consumption, significant weight and size characteristics and the relatively high cost of the station.

The prototype of the invention is a method of transmitting information, implemented in a satellite communications station of the enterprise CJSC Polyus, which contains a parabolic mirror antenna with a microwave unit and azimuth and elevation axis blocks, an antenna pointing unit, an indication device, a data input device, a computing device equipped with programs, including antenna pointing (O. P. Frolov. Antennas for satellite earth stations. - M.: Radio and communications, 2000, p. 260-265).

In this method, the antenna is programmed in elevation and azimuth to a given point in space. The operation of searching and capturing a signal by elevation and azimuth is also performed. After capturing the signal, the antenna is accurately guided to the signal source.

Software guidance of the antenna in elevation and azimuth is carried out by turning the antenna to the angles calculated in the computing device from the basic measuring planes:

- horizon plane - for elevation;

- meridian planes - for azimuth.

The disadvantages of this method of transmitting information are the relatively high power consumption, significant weight and size characteristics and the cost of the equipment.

The objective of the invention is to simplify the equipment of the repeater, reducing its energy consumption, weight and size characteristics and cost. Reducing energy consumption is especially important when installing repeaters in remote areas where it is necessary to use autonomous sources of electricity, which significantly increases the mass, dimensions and cost of the repeater.

The technical result achieved in this case is to simplify the equipment of the repeater, reduce its energy consumption, reduce weight and dimensions.

To achieve the technical result, a method for transmitting information is proposed, which includes software pointing the receiving antenna of the repeater to the signal source by turning the receiving antenna in elevation and azimuth to the program angle, followed by precise pointing to the signal source, as well as software pointing the transmitting antenna of the repeater to the subscriber station in accordance with the calculated azimuth and elevation angle, while before the software turn of the receiving antenna in elevation to the signal source there is a scaling mode in which the receiving antenna is rotated in elevation by the calculated angle and its position is fixed, and the rotation is performed in the second speed mode, which is 4-10 times less than the speed of the first mode, after which the calculated angle is compared with the computing device the actual value of the angle, measured using the elevation scale of the receiving antenna and entered into the computing device, as a result of which the correction for the angular velocity is determined, which is taken into account when frame rotation of the receiving antenna in elevation in the second speed mode, then on the display devices display the calculated elevation angles of the signal source and subscriber station, then programmatically rotate the receiving antenna to the signal source in elevation and fix its position, the rotation is carried out in the first speed mode if the value of the program elevation angle is greater than the calculated boundary value, or in the second speed mode, while, in accordance with the calculated value displayed on the display device, using the elevation angle of the signal source and indicating the elevation scale of the receiving antenna, one or two corrections are made to the position of the receiving antenna to bring the elevation angle to the calculated value and fixing this position of the receiving antenna, then the scaling mode of the receiving program antenna’s turn in azimuth is similar to the elevation angle scaling mode , then the receiver antenna is turned in azimuth in the first speed mode, the maximum value of the signal emitted by the source is measured m of the signal, after which, after a specified angle after passing through the maximum signal value, the receiving antenna is stopped and its position is fixed, then the receiving antenna is rotated in the second speed mode in the opposite direction, and its position is stopped and fixed when the signal is increased to a boundary value of 30 to 70 percent of the maximum value, the azimuth value measured using the azimuthal scale of the receiving antenna is introduced into the computing device, after which the receiving antenna is rotated s in the second speed mode in the same direction with stopping and fixing its position through a given angle with passing the maximum signal value and the second boundary value equal to the first, after stopping, rotate the receiving antenna in the opposite direction in the second speed mode with stopping and fixing the position at increasing the signal to the second mentioned boundary value, the azimuth value measured using the azimuthal scale of the receiving antenna is entered into the computing device from the two values found the azimuth of the computing device determines the azimuth of the signal source, which is used to program the transmitting antenna in azimuth to the subscriber station, and then display on the display devices the found azimuth of the signal source and the calculated azimuth of the subscriber station, then, in accordance with the azimuth of the source displayed on the display device the signal and the azimuthal scale of the receiving antenna, one or two corrections of the position of the receiving antenna are carried out with the azimuth brought to the found value reading and fixing this position of the receiving antenna, then the scaling mode of the transmitting antenna of the transmitting antenna in elevation is carried out similarly to the scaling mode of the software turning of the receiving antenna in elevation, then programmatically turning the transmitting antenna in elevation to the subscriber station and fixing its position is similar to software receiving antenna in elevation, in this case, in accordance with the calculated elevation angle of the subscriber displayed on the display device station and reading the elevation scale of the transmitting antenna, carry out one or two corrections of the position of the transmitting antenna to bring the elevation angle to the calculated value and fixing this position of the transmitting antenna, after which the scaling mode of the programmed turn of the transmitting antenna in azimuth is carried out similarly to the scaling mode of the turn of the transmitting antenna by angle places, then carry out a software turn of the transmitting antenna in azimuth to the subscriber station and fixation of its position similarly one-two rotation of the transmitting antenna in elevation, in accordance with the calculated azimuth of the subscriber station displayed on the display device and the azimuthal scale of the transmitting antenna, one or two corrections of the position of the transmitting antenna are carried out to bring the azimuth to the calculated value and fixing this position of the transmitting antenna then transmit the radio television signal.

The proposed method is implemented in the repeater through the use of special modes of pointing the receiving antenna to the signal source and transmitting antenna to the subscriber station. The method is illustrated by the functional diagram of the repeater shown in FIG. 1, the block diagram of the guidance modes of the receiving and transmitting antennas, shown in FIG. 2, the block diagram of the routine of the program turn of the receiving antenna from the initial position to the signal source at the elevation angle shown in FIG. 3.

The present invention relates to repeaters, characterized by a relatively low information transfer rate, having a relatively small mirror diameter and a relatively wide antenna pattern (of the order of 1.5-4 degrees). As an example, a repeater is considered having a radiation pattern width of the receiving and transmitting antennas of 120 arc minutes.

For frequencies of 3-6 GHz, the diameter of the repeater antenna is from 3.5 to 1.75 meters.

The accuracy of pointing the antenna with a power loss of 0.5 dB is considered sufficiently high, which corresponds to a pointing error of ± 0.2 of the antenna radiation pattern width. For the example in question, this corresponds to a pointing error of ± 24 arc minutes.

The repeater shown in Fig. 1 comprises a receiving antenna 1 on which a microwave unit 2 of the receiving antenna is mounted connected to a microwave unit 4 of the transmitting antenna located on the transmitting antenna 3. The microwave unit 2 and the microwave unit 4 are designed to convert the frequency, amplification and filtering of the relayed microwave signal. The second output of the microwave unit 2 of the receiving antenna is connected to the block 5 of the guidance of the receiving antenna, which is used to convert the microwave signal into a signal used for precise guidance of the receiving antenna 1. For control along the azimuth axis 6 of the receiving antenna, the relay includes a block 7 of the azimuthal axis of the receiving antenna, and for control along the elevation axis 8 of the receiving antenna, a block 9 of the elevation axis of the receiving antenna. For control along the azimuthal axis 10 of the transmitting antenna, the repeater comprises a block 11 of the azimuthal axis of the transmitting antenna, and for control along the elevation axis 12 of the transmitting antenna, a block 13 of the elevation axis of the transmitting antenna. Blocks 7 and 9 of the receiving antenna and blocks 11 and 13 of the transmitting antenna include drives that provide rotation of the axes, as well as brake clutches used to brake the antennas and fix their position.

At the receiving antenna 1 of the repeater installed azimuthal scale 14 of the receiving antenna and elevation scale 15 of the receiving antenna. An azimuthal scale 16 of the transmitting antenna and an elevation scale 17 of the transmitting antenna are mounted on the transmitting antenna 3 of the relay. The repeater also includes a computing device 18, designed to control the receiving antenna 1 and the transmitting antenna 3 and connected to the blocks 5, 7, 9, 11, 13. In addition, the relay includes a signal source elevation indication device 19 connected to the computing device 18 , a signal source azimuth indication device 20, a subscriber station elevation indication device 21, a subscriber station azimuth indication device 22, and a data input device 23. The receiving antenna 1 of the repeater is designed to amplify the received radio television signal 24 coming from the signal source, and the transmitting antenna 3 is used to amplify the emitted radio and television signal 25 coming from the repeater to the subscriber station.

Figure 2 shows a block diagram of the guidance modes of the receiving and transmitting antennas of the repeater: 26 - mode scaling software turn the receiving antenna in elevation; 27 - mode software rotation of the receiving antenna in elevation to the signal source; 28 is a mode of scaling the software turn of the receiving antenna in azimuth; 29 is a mode of the program turn of the receiving antenna in azimuth to capture the signal; 30 - the mode of precise guidance of the receiving antenna to the signal source in azimuth; 31 - mode of scaling the software turn of the transmitting antenna in elevation; 32 - software guidance of the transmitting antenna to the subscriber station in elevation; 33 is a mode of scaling the software turn of the transmitting antenna in azimuth; 34 - software guidance of the transmitting antenna to the subscriber station in azimuth.

Figure 2 shows the proposed guidance modes of the receiving and transmitting antennas, the use of which will ensure the receipt of the specified technical result. The flowchart reflects the sequence and relationship of modes.

When the repeater is installed and commissioned, its initial exhibition is carried out. In this case, usually with the help of washers and gaskets, as well as measuring tools (level, theodolite), the azimuthal axes of the antennas are displayed perpendicular to the horizontal plane. The azimuthal systems (zero azimuthal readings) of the receiving and transmitting antennas are mutually linked in the manufacture of the repeater using landing pins, if a common base for both antennas is used. With separate bases of the antennas, their azimuthal binding is carried out when the repeater is installed using the theodolite and technological mirrors. The binding of the azimuthal measuring system of the repeater to the meridian is carried out using additional technical means (magnetic compass, gyrocompass, radio compass, etc.).

The present invention allows to abandon the binding of the azimuthal measuring system of the repeater to the meridian and from additional technical means.

The repeaters in question are installed on a rigid base. The receiving antenna 1 receives the radio television signal 24 from the spacecraft or a ground source. The position of the ground source relative to the repeater does not change during operation. The accuracy of the position of modern spacecraft ("Express", "Hals") is high and amounts to 3-6 angular minutes. In connection with the above, with the required accuracy of pointing the receiving and transmitting antennas 1 and 3, it is enough to limit ourselves to the initial guidance of these antennas and fix the position of the antennas for the duration of operation until the next scheduled maintenance or repair. Fixing the position of the receiving and transmitting antennas 1 and 3 allows to increase the efficiency of the repeater, since the power supply to the guidance systems of these antennas is turned off.

In the proposed method, to ensure the required accuracy of pointing the receiving and transmitting antennas 1 and 3 at the level of ± 0.2 of the beam pattern, given the relatively wide radiation pattern of the considered transmitters, it is proposed to use a simpler antenna pointing system. Instead of the commonly used system with an angle sensor, which is a source of information about the position of the antenna, software control of the duration of the signal supplied to the DC motor, which rotates the antenna, is used. This will allow to abandon expensive equipment: angle sensors and information processing devices. This also simplifies the power supply.

The accuracy of working out the program angle is enhanced by repeated operations (corrections) in a semi-automatic mode using indicating devices and scales. This mode is acceptable, since the initial installation of the repeater, the exhibition of its axes and landing planes, its inclusion and data entry into the program is carried out by maintenance personnel.

Blocks 7, 9, 11 and 13 of the azimuthal and elevation axes of the receiving and transmitting antennas 1 and 3 are equipped with scales for visual determination of the angle of rotation of the corresponding axis. In radios with directional antennas, scales are usually used to solve technological problems. The error of the scale is not more than 10 arc minutes, which is quite acceptable for the repeaters in question.

To increase the speed and ensure the required accuracy of working out the program angle of the receiving and transmitting antennas 1 and 3, two modes are introduced: the first and second antenna rotation speeds. The first speed is used to work out large angles (up to 360 degrees). The transition to the second speed is carried out at a boundary angle, the value of which is entered into the memory of the computing device 18 in the manufacture of the repeater.

Software guidance of antennas usually consists of three stages: acceleration, steady state and braking. Antenna rotation includes only the stages of acceleration and deceleration, if the acceleration time is insufficient to reach the steady state.

At the same time, in particular, for the programmed turn of the antenna in elevation (ΔUM _P ), the following formulas are valid:

where ΔUM _p is the angle of rotation during acceleration, ΔUM _ur is the angle of rotation at steady state (constant turning speed), ΔUMt is the angle of rotation during braking.

With a linear model, the formulas can be used:

where ω _m is the maximum angular velocity of the antenna, Δt _yp , Δt _p , Δt _t are, respectively, the duration of the stages of the steady state, acceleration and braking.

In this linear model, it is assumed that the antenna speed varies linearly: during acceleration it increases, and during braking it decreases.

In a DC motor in steady state, the angular velocity of the rotor is proportional to the input voltage U. Therefore, the magnitude of the angle of rotation of the antenna (for example, elevation angle), determined from the formula

is proportional to the time interval Δt, which is found from the expression

In formulas (6) and (7) _and the proportionality factor K takes into account the static angular error.

Static error is determined by friction, power spread, losses in the rotor winding and other components. Dynamic error, first of all, is determined by the inertia of the drive (motor, gearbox) and antenna device. It is formed at the stages of acceleration and braking.

For the considered repeaters when using relatively large angular velocities (tens of degrees per second) when practicing small angles (1-5 degrees), the dynamic error is decisive. The introduction of the second speed mode solves the problem of increasing the accuracy of antenna pointing. For the considered repeaters, the speed of this mode is selected 4-10 times less than the speed of the first mode. In this case, the voltage supplied to the rotor winding is accordingly reduced. When working out large angles, the main one is the static angular error.

For braking and fixing the position of the receiving and transmitting antennas 1 and 3, it is proposed to use brake clutches. This can significantly reduce the error during braking of the antenna due to the reduction of the stop time (braking). For the repeaters under consideration, the braking time is 0.02 ± 0.02 seconds. The drive time constant is 0.03-0.1 seconds, and the antenna stop time after power off is 0.09-0.3 seconds.

The error in pointing the receiving antenna 1 to the signal source along the elevation angle is the sum of the horizontal error of the repeater, the location error (position uncertainty) of the signal source and the repeater, the error in working out the program angle, and the scale error. The most common case when the signal source is a spacecraft is considered.

Software guidance of the transmitting antenna 3 to the subscriber station in elevation is similar to pointing the receiving antenna 1. The difference is that for the transmitting antenna 3, the location error of the subscriber station and the repeater is taken. When using a satellite radio navigation system (GLONASS, GPS), this error usually does not exceed 6 arc minutes.

Pointing the receiving antenna 1 to the signal source in azimuth is carried out using the received signal. In this case, the pointing error consists of the error in determining the position of the maximum signal (this position corresponds to the azimuth of the signal source), errors in working out the given angle, scale errors, and errors in the spacecraft location.

Software guidance of the transmitting antenna 3 to the subscriber station in azimuth is characterized by a greater error. In the proposed method for binding to the meridian uses the direction of the receiving antenna 1 to the signal source. The error in the programmatic guidance of the transmitting antenna 3 to the subscriber station in azimuth is the sum of the errors in determining the position of the signal source in azimuth, the errors in the location of the spacecraft, the errors in the location of the subscriber station and repeater, errors in working out the program angle, and scale errors.

Let us analyze the accuracy of the software guidance of the receiving antenna 1 to the signal source by elevation. When the engine is turned on, there is a delay (time threshold) - the time during which the signal is not processed by the engine. It is due to the delay due to the inductance of the armature winding of the motor, as well as the delay of the switching circuit. If for the considered example we take the angular velocity of the first mode 30 deg / s, the time constant of 50 · 10 ^-3 seconds and the delay when you turn on 20 · 10 ^-3 seconds, then using the formula (4) can be found threshold for working out the corner during acceleration. We take for the acceleration time (it is equal to the delay time) Δt _p = 20 · 10 ^-3 s (40% of the time constant) the value ω _m = 12 deg / s and we find ΔUM _p = 7.2 angular minutes. This value ΔUM _p corresponds to the stage of acceleration without delay. If, for this case, at time Δt _p, braking is started using the brake clutch, then the braking angle ΔUM _{t is} added. With a maximum braking time of 0.04 s, from formula (5) we obtain ΔUM _t = 14.4 arc minutes. The addition of these two angles as random variables by the formula

gives the threshold angle for the first mode - 16.1 arc minutes.

This value is unacceptably large with a scale error of 10 arc minutes and a total error of 24 arc minutes.

In the second mode, when the angular velocity of the antenna is 3 deg / s, the threshold error decreases by a factor of 10. In this mode, the influence of static error increases significantly, since a decrease in the applied voltage and, accordingly, current increases the influence of the friction moment, as well as changes in the resistance of the armature winding due to temperature fluctuations. The scaling mode allows you to measure and compensate for the constant component of the static error. The angle specified in the program is compared with the actual worked angle. The found error is introduced as a correction to the computing device 18. The static error that remains after scaling is determined by a random spread of the friction moment, stress, and other factors. The total value of this error for the considered repeaters does not exceed 3-10 percent and is close to the static error of the first mode.

In the repeaters under consideration, during a fast program turn (first mode), there are three stages (acceleration, steady state and braking), therefore, formula (1) is valid. With a slow program turn (second mode), there can be either three stages or two stages (acceleration and deceleration). In the latter case, formula (2) is valid.

Given the formulas (1), (3), (4) and (5) the angle of rotation (elevation angle) of the antenna is found from the following formula

The duration of the program pulse Δt _pr formed in the computing device 18 is equal to (Δt _p + Δt _ur ). The actual antenna rotation time, taking into account the inertial motion during braking, is (Δt _p + Δt _yp + Δt _t ).

Given formula (9), the time of the program pulse Δt _pr for a given program angle ΔUM _{pr is} found from the formula

It is taken into account that at the stages Δt _p and Δt _{t, the} average antenna rotation speed is 1 / 2ω _m .

In the linear model, the angular velocity during acceleration is found from the formula

where - Kω is a constant coefficient.

In the formulas (9, 10), with the linear model, the boundary value of the time of the acceleration stage Δt _p = Δt _{pg is taken} , at which the angular velocity reaches its maximum value.

Technical parameters ω _m , Δt _pg and Δt are determined and entered into the memory of computing device 18 in the manufacture of the repeater. In this example, Δt has a nominal value of 0.02 s and a spread of ± 0.02 s. The time Δt _{pg is} taken equal to 2τ = 0.1 s (τ is the time constant of the control loop).

Formula (2) is valid for Δt _pp ≤Δt _pg . In this case, the program pulse time Δt _pp is equal to Δt _p , and the rotation angle is found from the formula

For a given program angle ΔUM _pr, formula (12), taking into account formula (11), is reduced to the quadratic equation

From this equation find the duration of the program pulse

In this example, in the second mode (ω _m = 3 deg / s, Δt _t = 0.02 s), the boundary _angle Δt _pg = 0.1 s corresponds to the boundary angle ΔUM _prg = 0.18 deg. For a smaller value of the program angle ΔUM _pr from the formula (14) in the computing device 18 find Δt _pp = Δt _p .

The proposed method for transmitting information is implemented as follows. After applying the power to the repeater carry out mode 26 (figure 2) - scaling the software turn of the receiving antenna 1 when it is rotated in elevation.

In this case, a software turn of the receiving antenna 1 (Fig. 1) from the initial (transport) position to a predetermined elevation angle and fixing it in this position using the brake clutch.

The receiving antenna 1 is controlled using the computing device 18 and block 9. In this mode, the receiving antenna 1 is left in the initial position in azimuth, and the transmitting antenna 3 is left in elevation and azimuth.

The control is carried out by applying a constant voltage corresponding to the second (exact) mode to the rotor winding for a time interval specified by the computing device 18, which corresponds to the program angle. This angle value is entered into the computing device 18 in the manufacture of the repeater. After stopping the receiving antenna 1, the actual elevation angle value is measured using an elevation scale 15 and inputted into the computing device 18 using the data input device 23. In the computing device, the voltage correction is determined - the scaling factor K _m .

For example, with a signal voltage of 2.5 V, which is 0.1 of the signal voltage corresponding to the fast mode (25 V), the worked angle is less than the program angle by 15%. In the computing device 18 for a given engine, the signal value is corrected by 15%, i.e. increases from 2.5 V to 2.875 V. Thus, scaling is performed for the slow mode. In this example, K _m = 1.15.

In the block diagram of the subroutine of the computing device 18 shown in FIG. 3 (FIG. 1), operations are shown that allow the software to guide the receiving antenna 1 in elevation to the signal source. This routine is used when conducting modes 26 and 27 (figure 2).

In the manufacture of the repeater in the computing device 18 (figure 1) enter the following parameters (operation 35, figure 3):

MIND _and - the initial elevation angle of the receiving antenna 1;

ΔUM _g - the boundary angle of the turn of two modes (fast and slow);

ΔUM _d - the permissible error of working out the elevation angle;

ΔУМ _t - boundary turning angle for two ranges of the second (slow) mode (large and small angles);

ΔUM _m - the program elevation angle when scaling;

Δt _t is the braking time (average);

Δt _pg is the boundary acceleration time;

ω _t - maximum speed in the exact (second) mode;

ω _g - maximum speed in the rough (first) mode.

The value of the software elevation angle of the signal source UM _{pi is} found and entered into this subprogram (operation 36, FIG. 3) after entering navigation data into the computing device 18 (FIG. 1) and before mode 26 (FIG. 2) is carried out.

The launch of the subroutine is performed in mode 26 with the execution of operation 37 (Fig. 3) - determination of the scaling pulse Δt _m in the computing device 18 (Fig. 1). Moreover, for a given angle ΔUM _m in the exact (first) mode from the formula (10) is the pulse duration Δt _m In the formula (10) it is accepted: Δt _pp = Δt _m , Δt _p = Δt _pg , ΔUM _pr = ΔUM _m , ω _m = ω _t . This pulse is fed to the rotor winding for processing the scaling angle ΔUM _m . Then, in the same mode 26 (Figure 2) the operation is carried out 38 (Figure 3) - input to the computing device 18 (Figure 1) via the input device 23 the actual angle values of the data space ΔUM _mf receiving antenna 1 after execution of the angle scaling.

According to the difference between the program and actual values of the elevation angle in the computing device 18, a correction is determined and entered into the memory — the scaling factor K _m (operation 39, Fig. 3). In addition, in this operation, the angle of the programmed turn of the receiving antenna 1 (Fig. 1) to the signal source according to the elevation angle is calculated by the formula

After that, carry out mode 27 (figure 2) - a software turn of the receiving antenna 1 (figure 1) in elevation to the signal source.

Entering into the computing device 18 navigation data characterizing the position of the repeater, the signal source and the subscriber station, the calculation according to these data of the programmatic elevation angles of the signal source and the subscriber station is carried out before mode 26 (Fig.2). Before the software turn of the receiving antenna 1 (Fig. 1), the calculated signal angle of the signal source is displayed on the signal source in the elevation device 19 on the indication device, and the calculated elevation angle of the subscriber station is displayed on the display device 21.

In the computing device 18, the rotation mode is determined (operation 40, FIG. 3): the value ΔUM _{pi is} compared with the boundary angle ΔUM _g

The threshold value ΔUM _g is determined on the basis of minimizing the turn time of the receiving antenna 1 (figure 1). For the considered example of a repeater, the ΔUM _g value should be units of degrees. In the proposed method, the angle ΔUM _g corresponds to the duration of the boundary pulse Δt _rg in the first (fast) mode. In this example, when ω _m = 30 deg / s, Δt _pg = 0.1 s and Δt _t = 0.02 s (Δt _yp = 0), the boundary value of the angle is determined from formula (12)

UM _g = 1.8 degrees.

In practice, a significant part of the time of program guidance is occupied by correction operations, which include: entering into the computing device 18 the value of the angle taken from the scale, determining and working out the difference between it and the program angle. Therefore, the number of corrections should be minimal.

If condition (16) is fulfilled, then at the command of computing device 18, a quick turn of the receiving antenna 1 and its braking with the help of a brake clutch are performed. The time of this quick turn Δt ₁ by the angle ΔУМ _пр in the computing device 18 is found from formula (10) (operation 41, Fig. 3). In this case, the angular velocity corresponds to the rough (first) regime ω _m = ω _g . When ΔUM _pi ≤ΔUM _g use the slow (second) mode. In this case, operation 42 is performed (FIG. 3): determining the range of the angle worked out

If condition (17) is satisfied, then formula (1) is valid, i.e. a software roll includes three steps. If condition (17) is not satisfied, then formula (2) should be used for a two-stage turn.

In the first case, in the computing device 18 (Fig. 1), formula (10) is used to find the signal duration Δt ₂ (operation 43, Fig. 3). Moreover, the angular velocity ω _m corresponds to the exact (second) regime ω _m = ω _t . In the second case, formula (14) is used (operation 44).

When condition (16) is met after a quick turn of the receiving antenna 1 (Fig. 1) for a given pulse Δt ₁ , the actual value of the angle UM ₁ taken from scale 15 is compared with the programmed elevation angle of the source of the signal UM _pi displayed on the display device 19 . If they differ by a value that is less than the tolerance ΔUM _d then this mode 27 (figure 2) ends, i.e. correction is not carried out. The probability of such a case is very small. If the difference between the UM _pi and UM ₁ exceeds the tolerance, then the following operation is carried out - the angle UM ₁ is entered into the computing device 18 (Fig. 1) using the data input device 23 (operation 45, Fig. 3).

Then, in the computing device 18 (FIG. 1), an operation 46 (FIG. 3) is performed — determining the correction angle

After that, carry out the operation 47 - determining the mode of working out the correction angle ΔУM ₁ by comparing

If condition (19) is satisfied, then re-refine (unlikely case) the angle in the fast (first) mode (operations 41, 45, 46). If condition (19) is not satisfied, then the correction angle is worked out in the exact (second) mode, starting from operation 42, and ΔUM ₂ = ΔUM _{pi is} taken.

When working in this mode, after the end of operation 43, at the command of the computing device 18 (Fig. 1), the receiving antenna 1 is rotated in the exact mode and its subsequent braking is performed using the brake clutch.

Then compare the actual value of the elevation angle of the MIND ₂ , taken from the scale 15, with a given angle of the MIND _pi , displayed on the display device 19.

If the condition

is not executed, then mode 27 (figure 2) ends.

If conditions (20) are fulfilled, then the following operation is carried out - input into the computing device 18 (Fig. 1) of the angle UM ₂ using the data input device 23 (operation 48, Fig. 3).

Then, in the computing device 18 (Fig. 1), operation 49 (Fig. 3) is carried out — determining the correction angle

After this, a repeated operation 42 is carried out - determining the range of the angle worked out. If condition (17) is satisfied, then repeat step 43.

If condition (17) is not satisfied, then in computing device 18 (Fig. 1), operation 44 (Fig. 3) is performed.

Then, at the command of the computing device 18 (Fig. 1), a software turn of the receiving antenna 1 and its braking using the brake clutch are performed.

After that, the actual value of the elevation angle of the PA ₃ , taken from the scale 15, is compared with the program angle of the signal source of the PA _Pi . If the difference between the UM _pi and the UM ₃ does not exceed the tolerance ΔUM _d , then the mode 27 (figure 2) ends. If the difference between the UM _pi and UM ₃ exceeds the tolerance, then the following operations are performed sequentially: entering the angle of the UM ₃ into the computing device 18 (Fig. 1) using the data input device 23 (operation 50, Fig. 3) and determining the correction angle (operation 51 )

After that, in the computing device 18 (Fig. 1), the operation 44 (Fig. 3) is repeated; the signal duration Δt ₂ is determined using the formula (14).

Mode 27 (FIG. 2) ends when the difference between the MIND _pi and the actual elevation angle of the receiving antenna 1 (FIG. 1) does not exceed ΔUM _d .

Actually, for the considered repeaters, one or two corrections are carried out for each corner. In the given example, we take UM _pi = 40 degrees, the error in the steady state Δur is 3 percent, i.e. 1.2 degrees.

From formula (9) with ω _m = 30 deg / s, Δt _p = 0.1 s, Δt _t = 0.02 s, we find the acceleration angle ΔUM _p = 1.5 deg and the braking angle ΔUM _t = 0.3 deg.

We take the error of the acceleration angle Δ _p = 0.45 degrees (30 percent) and the error of the angle of braking Δ _t = 0.3 degrees.

The total angular error Δ _Σ is defined as the sum of random variables

and we find Δ _Σ = 1.33 deg.

Since the error Δ _{Σ is} less than the boundary value of the angle for the fast (first) mode (1.8 deg.), Then during the correction we use the exact (second) mode (ω _m = 3 deg / s, Δt _p = 0.1 s, Δt _p = 0.02 s).

We find ΔUM _p = 0.15 degrees, ΔUM _t = 0.03 degrees, while the angle of the steady state ΔUM _ur = 1.15 degrees. The error of the steady state is assumed to be 5 percent, i.e. 0.063 degrees The error Δp and Δ _{t are} respectively equal to 0.045 degrees and 0.03 degrees. Using the formula (23) we find the total error Δ _Σ = 0,083 degrees, which is within the tolerance. Thus, in this case, one correction was used.

For the considered example of the repeater, the total error of pointing the receiving antenna 1 (Fig. 1) to the signal source by elevation includes the above-mentioned random errors: non-horizontal error - not more than 5 arc minutes; the error of the location of the signal source for modern spacecraft is no more than 6 angular minutes, the error of working out the program angle is no more than 5 angular minutes, the scale error is no more than 10 angular minutes.

Thus, the total error determined by the addition of random variables is 13.6 arc minutes.

After the end of mode 27 (FIG. 2), mode 28 is carried out - scaling the software turn of the receiving antenna 1 (FIG. 1) in azimuth. The mode is performed similarly to mode 26 (figure 2). When the receiving antenna 1 (Fig. 1) is rotated by a given angle in azimuth, the elevation angle equal to the elevation angle of the signal source is maintained constant by means of a brake clutch.

For a programmatic turn in azimuth of the receiving antenna 1 (Fig. 1) according to the signals of the computing device 18, a drive located in the block 7 of the azimuthal axis of the receiving antenna is used. The turn is made around the azimuth axis 6.

After the end of mode 28 (figure 2) carry out mode 29 - software turn of the receiving antenna 1 (figure 1) in azimuth to capture the signal. Moreover, the elevation angle of the receiving antenna 1 is constant and equal to the elevation angle of the signal source. The azimuth reversal is carried out in the fast (first) mode.

The relatively high accuracy of pointing the receiving antenna 1 in elevation compared to the width of the radiation pattern allows one-line signal search in the elevation. Azimuthal reversal is carried out only with one calculated value of the elevation angle of the signal source.

In the General case, the angle of rotation of the receiving antenna 1 to capture the signal can reach 360 degrees. The introduction of this turn allows you to abandon the binding of the azimuthal measuring system of the repeater to the meridian and from additional equipment (magnetic compass, gyrocompass, radio compass), which is used for the initial determination of the meridian.

In the proposed invention, as a physically feasible azimuthal base direction, it is proposed to use the direction of the optical axis of the receiving antenna 1 to the signal source (terrestrial or spacecraft). In this case, the direction of the meridian, which is used in the guidance program of the transmitting antenna 3, is calculated. The angle ψ _is between the meridian and the direction to the signal source and the angle ψ _AC between the meridian and the direction to the subscriber station is found by the known coordinates (latitude and longitude) of the signal source (for the spacecraft, by the coordinates of the sub-satellite point), the subscriber station, and the relay.

When pointing the receiving antenna 1 to the signal source determine the angle A _ZIS . The angle AZ _AC required for the azimuthal pointing of the transmitting antenna 3 to the subscriber station (azimuth of the subscriber station) is found from the expression

The received radio television signal 24 (FIG. 1) from the signal source is detected using the receiving antenna 1. In the microwave unit 2, the microwave signal is converted: filtering, amplification, frequency change. After conversion, the signal is supplied to the receiving antenna pointing unit 5. Using this signal, the guidance loop of the receiving antenna 1 is realized by the received signal.

Using the block 5 and the computing device 18 measure and enter into memory the magnitude of the signal, record its maximum value. When the signal is reduced by 2-5 percent in the computing device 18, a command is generated to stop the receiving antenna 1 using the brake clutch after a predetermined time.

This time is chosen so that the voltage signal decreases by 4-5 times compared with the maximum value. This corresponds to the rotation of the receiving antenna 1 in azimuth from the position of the maximum signal value by an angle equal to the width of the radiation pattern at a level of 3 dB.

In this example, this angle is 2 degrees.

Then carry out mode 30 (figure 2) - the exact guidance of the receiving antenna 1 (figure 1) on the signal source in azimuth.

At the command of the computing device 18, the receiving antenna 1 is rotated in the opposite direction (towards the maximum signal) in a slow (second) mode with signal magnitude measurement. When the signal is increased to a boundary value of 30 to 70 percent of the maximum value, a command is generated in the computing device 18 to stop the receiving antenna 1 and fix its position using the brake clutch.

The boundary value of the signal is selected on a steep section of the radiation pattern to increase the accuracy of the operation.

After stopping the receiving antenna 1 from the azimuth scale 14, the azimuth value is taken and input to the computing device 18 using the data input device 23.

After that, at the command of the computing device 18, the receiving antenna 1 is rotated in a slow mode in the same direction by the calculated angle with the passage of the maximum value and the second boundary value equal to the first. The stop and fixation of the position of the receiving antenna 1 is carried out using a brake clutch. This position corresponds to the rotation of the receiving antenna 1 in azimuth from the position of the maximum signal value by an angle equal to the width of the radiation pattern.

After stopping the receiving antenna 1 at the command of the computing device 18 spend its rotation in the opposite direction. The rotation is carried out in slow mode with the stop and fixation of the position of the receiving antenna 1 when the signal is increased to the second mentioned boundary value. After that, the azimuth value taken from the azimuth scale 14 is entered into the computing device 18.

The two azimuth values found in the computing device 18 determine the azimuth of the signal source as the half-sum of the two indicated angles. The found azimuth of the signal source is used for programmed guidance of the transmitting antenna 3 to the subscriber station in azimuth. The azimuth of the signal source is displayed on the display device 20, and the calculated azimuth of the subscriber station is displayed on the display device 22.

In accordance with the azimuth of the signal source displayed on the display device 20 and the azimuth scale of the receiving antenna 1, one or two corrections of the position of the receiving antenna 1 are performed in slow (second) mode, bringing the azimuth of the receiving antenna 1 to the found value. In this case, the operations shown in Fig. 3 (slow mode) are used.

After the correction is completed, the position of the receiving antenna 1 is fixed using a brake clutch.

For the considered example of the repeater, the total error of pointing the receiving antenna 1 to the signal source in azimuth includes the following random errors: position of the spacecraft - 6 arc minutes, scales - 10 angular minutes, working out of the program angle - 5 angular minutes, and also the error of the azimuth of the signal source. The last error includes a scale error (10 arc minutes) and an error when braking the receiving antenna 1. Since braking is performed in opposite directions, the braking error is compensated. Therefore, the error in the position of the maximum signal value is determined for a half-sum of random errors (scales) and is 7 angular minutes.

The total error in pointing the receiving antenna 1 in azimuth to the signal source is 14.5 arc minutes.

Then carry out the mode 31 (figure 2) - scaling the software turn of the transmitting antenna 3 (figure 1) in elevation. The mode is carried out similarly to the scaling mode of the software turn of the receiving antenna 1 in elevation.

After that, carry out the mode 32 (figure 2) - software guidance of the transmitting antenna 3 (figure 1) to the subscriber station in elevation. This mode is performed similarly to mode 27 (FIG. 2) using a similar subroutine. At the same time, in accordance with the calculated elevation of the subscriber station displayed on the display device 21 (FIG. 1) and the reading of the elevation scale 17, one or two corrections of the position of the transmitting antenna 3 are carried out, bringing the elevation angle to the calculated value and fixing this position of the transmitting antenna 3 using the brake clutch.

The accuracy of the software pointing the transmitting antenna 3 to the subscriber station in elevation is similar to the accuracy of pointing the receiving antenna 1 in elevation to the signal source.

After that, carry out the mode 33 (figure 2) - scaling the software turn of the transmitting antenna 3 (figure 1) in azimuth. The mode is produced similarly to the scaling mode of the software spread of the transmitting antenna 3 in elevation.

Then carry out the mode 34 (figure 2) - software guidance of the transmitting antenna 3 (figure 1) to the subscriber station in azimuth. This mode is performed similarly to mode 32 (figure 2) using a similar subroutine.

Moreover, in accordance with the calculated azimuth value of the subscriber station displayed on the display device 22 (Fig. 1), as well as the azimuthal scale 16 of the transmitting antenna 3, one or two corrections of the position of the transmitting antenna 3 are carried out, bringing the azimuth to the calculated angle value. After which the position of the transmitting antenna 3 is fixed using a brake clutch.

For the considered example of the repeater, the total error of pointing the transmitting antenna 3 to the subscriber station in azimuth includes the following random errors: the position of the spacecraft is 6 angular minutes, the azimuth of the signal source is 7 angular minutes, the location of the relay and subscriber station is 6 angular minutes, the working out of the program angle is 5 angular minutes, scales - 10 angular minutes. The total error is 15.7 arc minutes.

After executing mode 34 (FIG. 2), to reduce power consumption during operation, power is removed from the control equipment by elevation and azimuth of the receiving antenna 1 (FIG. 1) and transmitting antenna 3. After that, the radio-television signal is transmitted to the subscriber station.

The above description of the proposed method allows the following conclusion.

According to the assessment, due to the simplification of the equipment (the exclusion of angle sensors and devices for processing signals of the receiving and transmitting antennas, as well as a meridian detection device, for example, a radio compass, simplification of power supplies), the cost of one repeater set is reduced by 5000-10000 cu The mass of the repeater is reduced by 8-15 kg. If the repeater is powered from an autonomous source, then due to the reduction in energy consumption, the mass, dimensions and cost of this source are significantly reduced.

By simplifying the equipment of the repeater, as well as fixing the position of the receiving and transmitting antennas after pointing them, it is estimated that the power consumed during operation of the repeater is reduced by 20-30 percent.

Claims (1)

A method of transmitting information, including software pointing the receiving antenna of the repeater to the signal source by turning the receiving antenna in elevation and azimuth to the program angle, followed by precise pointing to the signal source, as well as software pointing the transmitting antenna of the repeater to the subscriber station in accordance with the calculated azimuth and elevation angle, characterized in that prior to the software turn of the receiving antenna in elevation to the signal source, a zoom mode is performed, in which the receiving antenna is rotated in elevation by the calculated angle and its position is fixed, and the rotation is performed in the second speed mode, which is 4-10 times less than the speed of the first mode, then the calculated angle is compared with the actual angle value measured with using the elevation scale of the receiving antenna and entered into the computing device, as a result of which the correction for the angular velocity is determined, which is taken into account when the receiving antenna is rotated by the elevation software in the second speed mode, then on the display devices the calculated elevation angles of the signal source and subscriber station are displayed, then the receiving antenna is programmed to the signal source by the elevation angle and its position is fixed, the rotation is performed in the first speed mode if the elevation program angle is greater calculated boundary value, or in the second speed mode, while in accordance with the calculated value of the elevation angle of the signal source and the angle of the local scale of the receiving antenna, one or two corrections of the position of the receiving antenna are carried out, bringing the elevation angle to the calculated value and fixing this position of the receiving antenna, then the scaling mode of the receiving antenna’s turn in azimuth is carried out similar to the scaling mode in elevation, then the receiving antennas in azimuth in the first speed mode, measure the maximum value of the signal emitted by the signal source, and then through a given angle after p When the maximum signal value is reached, the receiving antenna is stopped and its position is fixed, then the receiving antenna is rotated in the second speed mode in the opposite direction, and its position is stopped and fixed when the signal is increased to a boundary value of 30 to 70% of the maximum value, it is introduced into the computational the azimuth value measured using the azimuthal scale of the receiving antenna, then rotate the receiving antenna in the second speed mode in the same direction from the stop th and fixing its position through a predetermined angle with the passage of the maximum signal value and the second boundary value equal to the first, after stopping, rotate the receiving antenna in the opposite direction in the second speed mode with stopping and fixing the position when the signal increases to the second mentioned boundary value, enter computing device, the azimuth value measured using the azimuthal scale of the receiving antenna, the azimuth is determined from the two azimuth values found in the computing device and the source of the signal, which is used to program the transmitting antenna in azimuth to the subscriber station, then display on the display devices the found azimuth of the signal source and the calculated azimuth of the subscriber station, then, in accordance with the azimuth of the signal source displayed on the indicating device and the azimuth scale of the receiving antenna , carry out one or two corrections of the position of the receiving antenna, bringing the azimuth to the found value and fixing this position of the receiving antenna, after this, the scaling mode of the transmitting antenna of the transmitting antenna in elevation is carried out similarly to the scaling mode of the turning of the receiving antenna of the receiving antenna in elevation, then the program is rotated in the transmitting antenna in elevation to the subscriber station and fixing its position is similar to the programmatic rotation of the receiving antenna in elevation, while in accordance with the calculated elevation of the subscriber station displayed on the display device and the reading of the elevation scale of the transmitting antennas one or two corrections of the position of the transmitting antenna are carried out, bringing the elevation angle to the calculated value and fixing of this position of the transmitting antenna, then the scaling mode of the programmed turn of the transmitting antenna in azimuth is carried out similarly to the scaling mode of the programmed turn of the transmitting antenna in elevation, then a program turn is performed transmitting antenna in azimuth to the subscriber station and fixing its position is similar to the software rotation of the transmitting antenna in elevation, p Moreover, in accordance with the calculated azimuth of the subscriber station displayed on the display device and the azimuthal scale of the transmitting antenna, one or two corrections of the position of the transmitting antenna are carried out, bringing the azimuth to the calculated value and fixing this position of the transmitting antenna, then the radio-television signal is transmitted.

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