The device for evaluating characteristics of the zone of the initial search communications spacecraft

 

Application: specialized computer equipment for research process of detecting and tracking of spacecraft for communications with ground stations. The technical result is the extension of functionality by providing the possibility of using the device for the study of the process of detecting and tracking of spacecraft for communication with ground stations and histograms of the distribution of the parameters of the search process. The inventive device contains four blocks of random numbers, the set of real orbital position of the spacecraft, the set of real geographic reference station, block the formation of the real orientation of the onboard antenna, block the formation of the real orientation of the terrestrial antenna, the one-shot generator of clock pulses, the counter clock pulses, the sensor prediction of the orbital position of the spacecraft, sensor georeferencing station, unit for calculating the spatial orientation of the on-Board antenna, the unit of calculation of the spatial orientation of the terrestrial antenna unit calculating line of sight “spacecraft-station”, nl is the attenuation coefficient, the first and second inputs connected to the outputs, respectively, block the formation of the histogram distribution. 1 C.p. f-crystals, 3 ill.

The invention relates to specialized computer equipment and can be used to estimate the characteristics of the search area and maintenance of communications spacecraft for communications with ground stations.

A device containing memory blocks, the switch, the decoder, the block counting arrays, elements, block element OR buffer memory block, the input block of memory and two groups of elements And [USSR author's certificate No. 1835543, CL G 06 f 15/20, 1990].

A disadvantage of the known device is its relatively narrow functionality.

The closest in technical essence to the present invention is a device containing connected in series generator of clock pulses, the counter clock and the register, as well as the sensor of random numbers, a logarithmic Converter, dividers, delay elements, the shaper function of consumption of the resource element OR adder blocks comparison, the multiplier, the pulse shaper, solee closest technical solution is its relatively narrow features, not allowing you to use it to assess the characteristics of the search area and maintenance of spacecraft for communications with ground stations.

The required technical result is to increase functionality.

The required technical result is achieved in that in a device for evaluating the characteristics of the zone of the initial search communication spacecraft, containing a clock and counter clock pulses, and the first block of random numbers entered second, third and fourth blocks of random numbers, the set of real orbital position of the spacecraft, the first input connected to the output of the first block of random numbers, the set of real geographic reference station, the first input connected to the output of the second sensor unit random number block the formation of the real orientation of the onboard antenna, first input connected to the output of the third sensor unit random number block the formation of the real orientation of the terrestrial antenna, a first input connected to the output of the fourth sensor unit of random numbers, one-shot, the input enable is output - connected to the input of the start clock pulses, the sensor prediction of the orbital position of the spacecraft, the input of which is connected to the information output of the counter clock pulses, and the output is connected to a second input of the block forming the actual orbital position of the spacecraft, sensor georeferencing station, the output of which is connected to a second input of the processing unit real geographic reference station, the unit of calculation of the spatial orientation of the onboard antenna, the first and second inputs connected to the outputs, respectively, of the sensor prediction of the orbital position of the spacecraft and sensor georeferencing station, and the output is connected to a second input of the processing unit of the real orientation on-Board antenna, the unit of calculation of the spatial orientation of the ground antenna, the first and second inputs connected to the outputs, respectively, of the sensor prediction of the orbital position of the spacecraft and sensor georeferencing station, and the output is connected to a second input of the block forming the actual orientation of the terrestrial antenna unit calculating line of sight “spacecraft-station, the first and the second the body of low device and block the formation of the real geographic reference station, the unit of calculation of the penalty guidance on-Board antenna, the first and second inputs connected to the outputs, respectively, of the block of calculation of line-of-sight “spacecraft-station” and block the formation of the real orientation on-Board antenna, the unit of calculation of the penalty guidance terrestrial antenna, the first and second inputs connected to the outputs, respectively, of the block of calculation of line-of-sight “spacecraft-station” and block the formation of the real orientation of the terrestrial antenna, the unit of calculation of the attenuation coefficient, the first and second inputs connected to the outputs, respectively, unit calculating a miss-guided on-Board antenna and unit calculating a miss-guided ground antennas, and also block the formation of the histogram distribution, the first input connected to the output of the block of calculation of the attenuation coefficient, second, third and fourth inputs connected, respectively, with the output clock pulses from the output of the overflow of the counter clock pulses and output the one-shot, and the output is an output device for evaluating characteristics of the zone of the initial search communication spacecraft, in this case, the output of the overflow counter of clock pulses connected with in what you eat, that block formation of the histogram distribution contains a group of (n+1) units of comparison, the first inputs of which are combined and the first input of the processing unit of the histogram distribution, the second inputs are the inputs of the boundary interval distribution, a n - number of intervals allocation block of n elements And the first and the second input of each of which is connected to the output, respectively, of the same name and subsequent blocks comparison blocks comparison, the third inputs are combined and a second input unit of the formation of the histogram distribution, the block of n pulse counters, counting input of each of which are connected to the outputs of the same elements And block elements, And inputs setup to zero and United are fourth input of the unit forming the histogram distribution, and the block of n memory registers, information inputs each of which is connected to the same outputs of the pulse counter unit counts the pulses, the control input record are combined and the third input of the block forming the histogram distribution, and the inputs setup to zero combined with inputs installed in the zero pulse counters block counters.

In Fig.1 is yazno spacecraft in Fig.2 - unit forming a histogram of the distribution of Fig.3 - scheme of the process of finding and maintenance.

The device (Fig.1) device for evaluating characteristics of the zone of the initial search communication SPACECRAFT) contains the first 1, second 2, third 3 and fourth 4 blocks of random numbers, unit 5 forming the actual orbital position of the SPACECRAFT, the first input connected to the output of the first block 1 random number, unit 6, the formation of the real geographic reference station, the first input connected to the output of the second unit 2 generating random numbers, block 7 the formation of the real orientation on-Board antenna, the first input connected to the output of the third block 3 random number, unit 8 the formation of the real orientation of the terrestrial antenna, a first input connected to the output of the fourth block 1 random number, the one-shot 9, the input to the inclusion of which is a starting device for evaluating characteristics of the zone of the initial search communication spacecraft, the generator 10 clock pulses (GTI), the starting of which is connected to the output of one-shot 9, the counter 11 clock pulses, a counting input connected to the output of the GTI 10, and the d which is connected with the information output of the counter 11, and the output is connected with the second input unit 5 forming the actual orbital position of the SPACECRAFT.

The device (Fig.1) to characterize the zone of the initial search communication SPACECRAFT) also contains the sensor 13 geographic reference station, the output of which is connected with the second input unit 6 forming the real geographic reference station, unit 14 for calculating the spatial orientation of the on-Board antenna, the first and second inputs connected to the outputs, respectively, of the sensor 12 and sensor 13, and the output is connected to a second input of the block 7 to the formation of the real orientation of the onboard antenna and the unit 15 for calculating the spatial orientation of the terrestrial antenna, the first and second inputs connected to the outputs, respectively, sensor 12 and sensor 13, and the output is connected with the second input unit 8 forming the real orientation of the terrestrial antenna.

The device (Fig.1) device for evaluating characteristics of the zone of the initial search communication SPACECRAFT) further comprises a block 16 of calculating line-of-sight “spacecraft-station”, the first and second inputs connected to the outputs, respectively, of block 5 of the formation of real orbital position kasavetia on-Board antenna, the first and second inputs connected to the outputs, respectively, of the block 16 calculate line of sight “spacecraft-station and unit 7 the formation of the real orientation of the onboard antenna unit 18 calculation of penalty guidance terrestrial antenna, the first and second inputs connected to the outputs, respectively, of the block 16 calculate line of sight “spacecraft-station and unit 8 forming the real orientation of the terrestrial antenna unit 19 of the calculation of the attenuation coefficient, the first and second inputs connected to the outputs, respectively, unit 17 calculation of a miss-guided on-Board antenna unit 18 calculation of penalty guidance terrestrial antenna, and the block 20 forming the histogram distribution, the first input connected to the output unit 19 calculation of the attenuation coefficient, second, third and fourth inputs connected, respectively, with the output of the generator 10 clock pulses, the output of counter overflow 11 clock pulses and output the one-shot 9, and the output is an output device for evaluating characteristics of the zone of the initial search communication spacecraft, while the output of the counter overflow 11 clock pulses is connected to the stop input of the generator is in 21-1...21-(n+1), the first inputs of which are combined and the first input of the block 20 forming the histogram distribution, the second inputs are the inputs of the boundary interval distribution, a n - number of intervals allocation unit 22 elements 22-1 And...22-n, the first and second inputs each of which 22-i (i=1, n) connected to the output, respectively, of the same name 21-i and the subsequent 21-(i+1) blocks of the comparison group 21, the third inputs are combined and the second input unit 20 forming the histogram distribution, block 23 counter 23-1 to 23-n of the pulse counter inputs which are connected to the outputs of the same elements And block elements, And inputs setup to zero and United are fourth input unit 20 forming the histogram distribution, and the block 24 memory registers 24-1 to 24-n, the information inputs are connected to the same outputs of the pulse counter unit 23, the control input record are combined and the third input unit 20 forming the histogram distribution, and the inputs setup to zero combined with inputs installed in the zero pulse counters block 23 meters.

The diagram of the search process and maintenance (Fig.3) presents the real position 25 of the spacecraft, the actual position 26, ealee position 29 of the line of sight “spacecraft-station”, as well as coordinate system and the binding parameters of SPACECRAFT and ground stations to the respective coordinate axes.

Operating device for evaluating characteristics of the zone of the initial search communication SPACECRAFT) as follows.

Preliminary will conduct theoretical basis of his work.

Well-known difficulties of establishing and maintaining communication ground stations with moving objects in space radio links are complemented by a number of specific factors of the deterministic and random nature (the Earth's rotation, the uncertainty of the spatial position of the SPACECRAFT, inaccuracies orientation of airborne and ground-based antennas, etc), contributing to the uncertainty of the spatial position of the SPACECRAFT relative to the ground station. As a result, the position of the SPACECRAFT at the beginning of the communication session and in the course of inspection is random.

The area of uncertainty of the spatial position of the AC generated a total impact of complex uncertainties, the main ones are:

the uncertainty due to inaccurate prediction of the orbital motion of the SPACECRAFT;

newpreteen the certainty orientation on-Board antenna.

Characteristics of these uncertainties are described by the known laws of distribution of random variables and are the source data for estimating parameters of deviation of the actual line of sight on-Board and ground-based antennas from its calculated position during a communication session.

The adopted model of the spatial orientation of the SPACECRAFT relative to the ground station taking into account the spatial orientation of the ground and on-Board antennas and directional diagrams, allowing us to obtain formulas for the calculation of the power ratio at the input of the receiver stations and to assess the sustainability and reliability of communications, explained in Fig.3, where the following symbols are used:

And, KZ, Uz, Z - geocentric coordinate system;

25, 26 - spacecraft and ground station, respectively;

27, 28 - beam airborne and ground-based antennas, respectively, the Central axis of which determine their exposed line of sight;

29 is a real line of sight “KA - station”;

and,c - inclination angles of the exposed lines of sight on-Board and ground-based antennas, respectively, from the real line of sight is p>For validation of the mathematical model used the following assumptions about the sources of uncertainty of the initial position of the line of sight “KA - station”:

errors determine the position of the SPACECRAFT and the station in the geocentric coordinate system;

errors prompting on-Board antenna in the orbital coordinate system;

errors pointing ground-based antennas in the station coordinate system.

In addition, we assumed that the orbital plane of the SPACECRAFT passes through the point of location of the ground station, and pattern of on-Board and ground-based antennas relied axisymmetric and their descriptions were used approximation of the form

where Z=(2/)Rsin; R is the radius of the mirrors;- the angle of deviation of the line of observation of the direction of maximum radiation pattern.

Power ratio at the input of the receiver station at the coincidence of the maxima of the radiation patterns of the onboard and ground-based antennas was determined by the ratio signal/noise

and along the real line visitatio, G, DPR - gain-Board and ground-based antennas; Cs.Leff is the effective noise power at the input of the receiving device; Lthe attenuation of the signal on the track of the radio link; X=X(a,c) the attenuation of the signal due to the mismatch of the maxima of the radiation patterns of the onboard and ground-based antennas.

In the calculations it was assumed that the error in determining the position of the SPACECRAFT and stations are subject to the normal law with known characteristics. It is assumed that the position of the SPACECRAFT is calculated in the mobile orbital coordinate system and the allowable error of prediction of the position of the SPACECRAFT with long-term planning depends on the forecasting interval.

In the proposed device for research of the search process, guidance and support KA in the process of communication with the ground station used method of statistical simulation.

The described approach to the study of this process is implemented as follows.

In General, when describing the search process in three-dimensional space (Fig.3) each of the units 1 to 4 can be performed and are the input of the corresponding block, and outputs constitute the output of the corresponding block. Each sensor is intended for input random amendments to the corresponding spatial coordinate describing the orbital position of the SPACECRAFT, the geographic location of the station or the results of the calculation of the spatial orientation airborne or terrestrial antenna. Sensor 12-13 can be made in the form of ROM blocks 5-8 - in the form of three parallel on respective coordinates of adders, blocks 14-19 - in the form of a ROM. Information about the operation of the device, below, is sufficient for programming the ROM.

Before starting the device, the counter 11 is set to the desired initial position, for example, the conditional time the SPACECRAFT is in orbit at a given point of space. Run the device begins to supply power to the input of one-shot 9, generated by the pulse which is used to run the GTI 10, as well as zeroing in block 20 forming histograms counter unit 23 and the register unit 24. The counter 11 clock pulses produces the formation of the current time (time samples) t research (finding a SPACECRAFT in orbit). These temporary timing sensor 12 produces the formation trentadue means unessecery measurements (in the particular case, in the evaluation of the search area when entering a relationship these coordinates are constants that determine the spatial position of the SPACECRAFT in three-dimensional coordinate system). Synchronously with the formation of a timing pulse survey changes the state of the outputs of the random number included in block 1. As a result, the output unit 5 sequentially in time are formed three coordinates corresponding to the actual orbital position of the SPACECRAFT. At the output of the sensor 13 is continuously being shaped by three coordinates Xc(t) Yc(t), Zc(t), describing the geographic location of the ground station. This information can be obtained from the results of geodetic measurements. Therefore, when a similar (described above) status outputs of the random number included in block 2, the output unit 6 sequentially in time are formed three coordinates corresponding to the actual geographical position of the ground station. The signals from the outputs of the sensor 12 and the sensor 13 in the block 14 is formed information about the spatial orientation of the pattern on-Board antenna. The calculations in this block can be performed using standard ratios of analytical geometry, which allows to determine in normiruemoy in three coordinates on the output of the sensor 12, and the point georeferencing ground station, which is formed in the form of three coordinates on the output of the sensor 13. The sensor unit 3 form a random amendments that change the coordinates, formed in the block 14, which allows you to generate the output unit 7 angular coordinates describing the real orientation of the on-Board antenna. Similarly, the signals generated by the sensors 12 and 13, block 15 is determined by the estimated spatial orientation of the antenna of the ground station, and the output unit 8 to its actual orientation. In block 16 on three coordinates generated by unit 5 and determines the actual orbital position of the SPACECRAFT, as well as three coordinates, generated by the block 6 and determining the actual position of the ground station calculates the real line 29 of sight “KA - station”. For the calculation can also be used standard correlation of analytical geometry, which allows to determine in the space of the angular direction of the straight line passing through the actual point of the orbital position of the SPACECRAFT and the point of actual geolocation of the ground station. The signals generated on the output unit 7 and the output of block 16, block 17 are calculated angleand, the characteristic is KA - station, and the signals from the outputs of the block 8 and 16 - calculation of anglewith deviations (miss) direction of a terrestrial antenna relative to the line of sight “KA - station”. In Fig.3 these deviations are indicated by means of corresponding anglesa andfor the case with the projection of the corresponding lines on the orbital plane passing through the point to the location of the ground station. To calculate these mistakes can also be used standard correlation of analytical geometry.

Assessment misses conducted in blocks 17 and 18, allows the value of the attenuation coefficient, which, in the particular case, is determined by the product of the two relations (1), calculated for anglewith and angleA.

Generated at the output of the block 19, the flow of possible values of the random variable characterizing the attenuation coefficient, is fed to the input of block 20 forming the histogram distribution. In this unit, each of the current output unit 19 is compared with the threshold levels of the blocks 21-i, each of which corresponds to the private boundaries of intervals partitioning the total interetested fact contact the appropriate interval, fixed the appearance of the clock pulse at the output of the corresponding element And the block 22 with a subsequent change of state of the counter unit 23. The contents of the counters corresponds to the registers unit 24 according to the output signal from the overflow of the counter 11 clock pulses, the maximum contents of which are calculated by the required number of statistical tests. As a result, the contents of the registers corresponds to the full histogram of the distribution of possible values of the attenuation coefficient. By varying the parameter values of the random number included in blocks 1-4 and characterizing the degree of influence of various random factors can be explored their influence on the dispersion of the values of the attenuation coefficient, and is defined, in particular, the requirements for precision pointing and tracking SPACECRAFT in the organization of the communication session.

If you specify a constant or a little time-varying signal at the output of the sensor 12, the research process will correspond to the capture mode AC mode of entering into a relationship.

If the information input unit 20 instead of the output signal of block 19 signal from block 17 or 18, the device allows you to generate a histogram of the distribution of misses Assirati functionality known technical solutions and to provide a study of the search process, capture and maintenance of AC in communication with the ground station.

Claims

1. The device for evaluating characteristics of the zone of the initial search communication spacecraft, containing a clock and counter clock pulses, and the first block of random numbers, wherein the entered second, third and fourth blocks of random numbers, the set of real orbital position of the spacecraft, the first input connected to the output of the first block of random numbers, the set of real geographic reference station, the first input connected to the output of the second sensor unit random number block the formation of the real orientation of the onboard antenna, first input connected to the output of the third sensor unit random number block the formation of the real orientation of the terrestrial antenna, a first input connected to the output of the fourth sensor unit of random numbers, one-shot, the entrance include of which is a starting device for evaluating characteristics of the zone of the initial search communication spacecraft, and the output connected to the input of the start generat the n information output counter clock pulses, and the output is connected to a second input of the block forming the actual orbital position of the spacecraft, sensor georeferencing station, the output of which is connected to a second input of the processing unit real geographic reference station, the unit of calculation of the spatial orientation of the onboard antenna, the first and second inputs connected to the outputs respectively of the sensor prediction of the orbital position of the spacecraft and sensor georeferencing station, and the output is connected to a second input of the processing unit of the real orientation on-Board antenna, the unit of calculation of the spatial orientation of the ground antenna, the first and second inputs connected to the outputs respectively of the sensor prediction of the orbital position of the spacecraft and sensor georeferencing station, and the output is connected to a second input of the block forming the actual orientation of the terrestrial antenna unit calculating line of sight “spacecraft-station”, the first and second inputs connected to the outputs respectively of the block forming the actual orbital position of the spacecraft and block the formation of the real geographic reference station, unit calculate the ka of calculating line-of-sight “spacecraft-station” and block the formation of the real orientation of the onboard antenna, the unit of calculation of the penalty guidance terrestrial antenna, the first and second inputs connected to the outputs respectively of the block calculating line of sight “spacecraft-station” and block the formation of the real orientation of the terrestrial antenna, the unit of calculation of the attenuation coefficient, the first and second inputs connected to the outputs respectively of the block of calculation of penalty guidance on-Board antenna and unit calculating a miss-guided ground antennas, and also block the formation of the histogram distribution, the first input connected to the output of the block of calculation of the attenuation coefficient, second, third and fourth inputs are connected respectively with the output clock pulses, with the release of the overflow of the counter clock pulses and output the one-shot, and the output is an output device for evaluating characteristics of the zone of the initial search communication spacecraft, while the output of the overflow counter of clock pulses is connected to the stop input of the clock.

2. The device under item 1, characterized in that the shaping unit of the histogram distribution contains a group of (n+1) units of comparison, the first inputs of which are combined and the first input of the block is formed the n - number of intervals allocation the block of n elements And the first and the second input of each of which is connected to the output respectively of the same name and subsequent blocks comparison blocks comparison, the third inputs are combined and a second input unit of the formation of the histogram distribution, the block of n counters pulse counter inputs each of which is connected to the outputs of the same elements And block elements, And inputs setup to zero and United are fourth input of the unit forming the histogram distribution, and the block of n memory registers, information inputs each of which is connected to the same outputs of the pulse counter unit counts the pulses, the control input record are combined and the third input of the block forming the histogram distribution, and the inputs setup to zero combined with inputs installed in the zero pulse counters block counters.



 

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