UA23213U - Channel for automated following of aircrafts by direction for laser information-measuring system - Google Patents

Abstract

The utility model relates to laser systems. Channel for automated following of aircrafts by direction for laser information-measuring system has control element, block for control of deflectors, laser with pumping, selector of longitudinal modes, block of deflectors, transmission optics, receiving optics, photodetector, wide-band amplifier (WA), resonance amplifiers adjusted to respective frequencies of inter-mode bits, detectors, filters, pulse formers, triggers ("1"|"0"), circuits "and", delay lines, counters, digital-analog transformers, low frequency filters, amplifiers (filters) of error signal, executive mechanisms, electronic-digital computer (EDC) and a - input of support signal with frequency ??M of transmission laser, b - input of signal from channel of evaluation of tangent component of velocity (angular velocities) of aircraft (A) to adjust error of coincidence by angles. For possibility to perform information inter-connection with A after WA information block is additionally included, this is connected to transmission optics for formation of information being transmitted and EDC for information received from A processing and representation.

Description

Description of the invention

The proposed useful model refers to the field of laser systems and can be used for 2 construction of the transmitting part of the laser information and measurement system (LIVS) with the modernized frequency-time method (MFCHM) of measurement.

The well-known "System of automatic tracking of an aircraft by direction on multimode lasers" (1), which contains a laser connected in series with a laser pump unit, a selector of longitudinal modes, transmitting optics, and for receiving a signal - receiving optics, a photodetector, resonant amplifiers, circuits 70 comparison, an error signal device, an executive device and can additionally be supplemented with channels for measuring the inclined distance K and the radial speed Ki. The system can provide auto-tracking of the aircraft (LA) by direction while simultaneously measuring K, K and azimuth and city angles.

The disadvantage of the known system is that it does not measure the angular speed of the aircraft, does not use this information to increase the stability (astatism) of the channel of the automatic tracking of the aircraft by direction (ASN) and does not use low-frequency filtering of the received signals in the ASN channel.

The closest to the proposed technical solution, chosen as a prototype, is the "Channel of automatic tracking of aircraft by direction based on the modernized time-frequency measurement method" |2), which includes a control element (KE), a deflector control unit (BKD), a pumped laser (Liu), longitudinal mode selector (SPM), deflector block (BD), transmitting optics (PRDO), receiving optics (PRMO), photodetector (FTD), broadband amplifier (SHP), resonance amplifiers (RP) tuned to the corresponding frequencies of intermode of bits, detectors (Det), filters (F), pulse shapers (FI), triggers

C1710U, circuits "and" (7, delay lines (LZ), counters (Le), digital-to-analog converters (DAC), low-pass filters (LFF), amplifiers (filters) of the error signal (PSF), executive mechanisms (VM) , electronic differential computing machine (EDCOM) and.а - input of a reference signal with a frequency of Lu 29 of the transmitting laser, b - input of a signal from the channel for evaluating the tangential component of the speed (angular velocities) of the aircraft to clarify the error of coincidence along the corners.

The shortcoming of the prototype system is that the ASN channel does not communicate information with the LA.

The basis of the useful model is the task of creating a channel for automatic tracking of aircraft by direction for the laser information and measurement system, which will allow for 3o information communication with the aircraft and its accurate and stable angular auto-tracking while simultaneously measuring the angles of azimuth A and city B in a wide range of distances, starting from the initial moment of the LA flight. see

The problem is solved due to the fact that the known prototype system |21) contains a control element, a deflector control unit, a pumped laser, a selector of longitudinal modes, a deflector unit, transmitting optics, receiving optics, a photodetector, a broadband amplifier, resonant amplifiers tuned to the appropriate frequencies of intermode bits, detectors, filters, pulse shapers, flip-flops (1710, "ii" circuits, delay lines, counters, digital-to-analog converters, low-pass filters, amplifiers (filters) of the error signal, executing mechanisms, an electronic differential computing machine and a - input of a reference signal with the frequency of Luu, a transmitting laser, b - input of a signal from the evaluation channel -o of the tangential component of the velocity (angular velocities) of the aircraft to clarify the error of coincidence along the corners, additionally c after the SP an informational block (IB), which is connected to the PRDO for the formation of the transmitted and ECOM for processing the information received from the aircraft and its display.

The construction of the channel of automatic tracking of aircraft by direction for the laser information-measuring system is connected with the use of МЧЧМ measurement |З| and single-mode 7 high-frequency laser radiation.

The technical result that can be obtained in the implementation of a useful model consists in the implementation of (95) information communication with the aircraft and its stable angular tracking and simultaneous high-precision 7 measurement of the angles of azimuth A and city B in a wide range of distances starting from the initial moment of the flight of the aircraft at extra-narrow DS. Fig. 1 shows a generalized structural diagram of the proposed channel for automatic tracking of aircraft "c" by direction for a laser information and measurement system, where a - input of a reference signal with the frequency Luu (Zluu) of the transmitting laser, b - input of a signal from the evaluation channel of the tangential component of the velocity (angular velocities) A" (B') LA to clarify the coincidence error along the corners of the channels.

Fig. 2 shows the creation of an equal signal direction and scanning of 4 DS in orthogonal planes.

Fig. 3 shows voltage graphs from the outputs of the blocks of the proposed ASN channel for the laser information and measurement system.

Figure 4 shows the voltage graphs from the outputs of the blocks of the proposed ASN channel for the laser information and measurement system, which determine the polarity, where a) for determining the sign "--", b) for determining the sign and

Figure 5 shows the angle of deviation of LA from RON relative to LEVS.

The proposed channel of automatic tracking of aircraft by direction for a laser information and measurement system contains a control element, a deflector control unit, a pumped laser, a longitudinal mode selector, a deflector unit, transmitting optics, receiving optics, a photodetector" 65 broadband amplifier, resonant amplifiers tuned to the appropriate intermode bit frequencies, detectors, filters, pulse shapers, triggers ("1"71"07U, circuits "and", delay lines, counters,

digital-to-analog converters, low-pass filters, amplifiers (filters) of the error signal, executing mechanisms, an electronic-digital computer and a - input of a reference signal with a frequency of lLuu, a transmitting laser, b - input of a signal from the channel for evaluating the tangential component of the velocity (angular velocities) of the LA to clarify the error of coincidence in the corners, the information block for the information relationship with

LA.

The operation of the proposed channel of automatic tracking of aircraft by direction for the laser information and measurement system is as follows.

From the synchronized single-mode multi-frequency radiation spectrum of the UAS: Ma Z - laser (Ln) 70 using the SPM, the necessary pairs of frequencies are isolated to create: - an information communication channel, under the condition of using a signal from the difference frequencies of intermode bits

DuzoitU1otu179Auu; - equal-signal direction based on the formation of the total DC, thanks to the partially intersecting 4 partial directional diagrams, provided that the difference frequencies of intermode beats are used

DuvdtUv'UdtAum Duottudtut 2 Lum

DuvatUv'UuzUZAum; Dudo-uvtu"- boom:

The signal with the frequency of intermode beats of the UDum, bypassing the DB, gets to the PRDO, where it mixes with the signal from the IS and forms the transmitted information for the LA (Fig. 1, 2).

Signal frequency of intermode beats Dumy 2Aum; Zlum and blue falls on the DB, which is made of 4 deflectors. Partial DSs scan the database in pairs in each of the two orthogonal planes (Fig. 1, 2).

The scanning period is set by the deflector control unit, which, together with Ln, is provided with the necessary power from the control element. Passing through the transmitting optics, a group laser pulse signal of pairs of frequencies: uvuudtAum: UuvuUTTaLUM: UviuzUZAUum; UviuotOAum; Ta uzom47U9Aum; (Fig. 1, 2) is focused in the scan of point 29 of the space, since counter scanning is carried out by two pairs of DS in each of the two orthogonal planes

A HER B or X and U (Fig. 2).

Received by the receiving optics, the information laser pulse signals reflected from the LA and in the process of scanning the four DS laser pulse signals and enveloping the DS signals with the help of a photodetector are converted into electrical pulse signals at the difference frequencies of intermode beats, amplified by a broadband amplifier, and distributed to the Shk in the Ulum information block for processing the received information from LA and on resonant amplifiers, -- built for the corresponding frequencies: Luu; 2Lum" ZLum and Bloom. At the same time, pulsed radio frequency signals that and c come from RPlLuu and RP2Auu - they form an error signal in the angle A, and RPZALuu and RPblu,y - in the angle B.

The formation of the error signal at angle A is as follows. co

Entering the pulse signal (a) from the reference channel Luu, transformed by FI! in "bundles" of reference pulses at the low frequency Lum op; goes to scheme "1". Separated and amplified pulse signal from RPduu of the frequency of Dumu intermode beats; (Fig. 3 and 4), Det is detected in the form of a signal envelope that changes according to the law of motion of the DC laser and, after passing through Ф, turns into Fi2 at the transition points of the scan periods into pulses (one pulse per scan period), enters the trigger "And" flipping it over. At the same time, selected and strengthened RPaldu; "pulse signal of the frequency of intermode bits 2Luu is detected by extracting the envelope of the signal, which changes according to the same law and, passing through Ф, is converted into FIiI2 at the points of transition of periods of oscillations into pulses (one pulse per scan period), enters the trigger "0 ", setting it to its original state. "» The task of measuring the time interval in the "I" scheme with a given accuracy is to establish the criterion for the beginning and end of the time interval count according to the determined characteristics of the value of the pulse signals arriving at the inputs of the "I" scheme. Due to the fact that the front the front of the pulse is quite small in comparison with the resolution that is required, in terms of time, the characteristic values of the signal that determine the beginning and end of the count from the time interval are the limit value y, (threshold value of the voltage) (Fig. 4).

Due to the periodic opening and closing of the "I" circuit by the trigger during the scanning cycle, the passage of pulses in the "I" circuit from FI!1 is regulated, i.e., there is a selection of "bundles" of pulses, the number of which is proportional to the angle 20 of the deviation of the LA from the RSN (Fig. 4 , 5). The pulses counted by the counter are converted by the digital-to-analog converter into an analog error signal with the required sign, which is mixed in the low-pass filter with the pulse signal from the channel of angular velocities of the LA (b) to clarify the coincidence error in the corners. Thanks to the accounting of measurement information from the channel of angular velocities (b), dynamic and fluctuating filtering errors (4) are eliminated in the low-pass filter. Filtered in the FNU and amplified by the error signal amplifier, the received signal is processed with the help of the executive mechanism (A), comes from the PSP, to the input of the ECOM and is allocated to it in the form of a number proportional to the measured azimuth angle A. c If the LA is above the RSN, then on circuit "I" is the first to receive an impulse from FI2 of the Lum intermode frequency; And the trigger receives a second pulse from FI2 of intermode frequency 2LuM (Fig. 1, 4). A strobe is applied to the circuit "I" from the trigger, the duration of which is proportional to the deviation of the LA from the RSN. This time interval is measured 60 by the method of counting pulses of the frequency of intermode beats Aum:

Since the duration of the strobe depends only on the amount of LA deviation from the RON, and not on the side of the deviation, it is necessary to have a scheme for determining the polarity of the error signal ("-" or "-3). Thus, if the LA will be located below the RSN, then the impulse from FiI2 will arrive first from the 2Aum channel, and the second - from the lLumu channel. The scheme for determining the sign or side of the LA deviation from the RON works according to Fig. 1, 4 a, 6. Because if the LA is above the RON, then pulse 1 (Fig. 1, 4 a) from channel Lu, ahead of the pulse of 2 channels 2lAuu.

Since the strobe from the trigger is delayed for a time that exceeds the duration of pulse 1 (or 2), the matching scheme "And" will not work, because pulse 1 will not coincide in time with this strobe. The sign of the angle A error signal remains positive.

If LA is below RON (Fig. 3 b), then pulse 1 lags behind pulse 2, so it coincides in time with the strobe. Circuit "I" activates and changes the sign (or polarity) of the voltage of the error signal along angle A. The pulse from circuit "I" is fed to the sign digit of the pulse counter with a frequency of Luu. The number of pulses in the counter is proportional to the angle of deviation of A from RON.

Formatting of the angle error signal B occurs in a similar way. Executive mechanisms of the VMA and 7/0. WWII, deploy the receiving and transmitting platform in such a way that the LA is located on the RON of the ASN channel, that is, on the RON of four partial DNs.

Display of received (transmitted) information from the aircraft and processing (measurement) of the angles of azimuth A and city B takes place in ECOM.

Sources of information: 1. Rondin Y.P., Kolomiytsev A.V. The system of automatic tracking of the object in the direction of multimode lasers. / Information systems. Vip. - 1(5). - Kh.: NANU, PAN, KhVU. - 1997. - P.35-39. 2. Declaratory patent for invention 59115 A, Ukraine, 7MPK (301517/42, (z01517/66. Channel of automatic tracking of aircraft by direction based on the modernized time-frequency measurement method. /" Alyoshin G.V., Kolomiytsev O.V ., Pashkov D.P. - Mo2003010713; Application. 01.27.2003; Publ. 08.15.2003;

Bul. Mo8. - 5s.

Z. Declaratory patent of Ukraine for an invention Mob5099А, Ukraine, (301517/42, (301517/66. Modernized frequency and ace method of measuring parameters of the movement of aircraft. / Kolomiytsev O.V. - Mo2003054908;

Application. 15.03.2004; Published on March 15, 2004; Bul. Mo3-4s. 4. Kolomiytsev A.V. Measurement of the tangential component of the speed of movement of the object. / Information processing systems. Vol. 1(5). - Kh.: NANU, PAN, KhVU. - 1999. - P.162-166. WITH

Claims (1)

The formula of the invention is the Channel of automatic tracking of aircraft according to the direction for the laser information and measurement system, which contains a control element, a deflector control unit, a pumped laser, a selector of longitudinal modes, a deflector unit, transmitting optics, receiving optics, a photodetector, a broadband amplifier ( SP), resonant amplifiers tuned to the appropriate frequencies of intermode bits, detectors, filters, pulse shapers, flip-flops ("1"71"07U, circuits "and", delay lines, counters, and digital-to-analog converters, low-pass filters, amplifiers (filters) of the error signal, executive mechanisms, an electronic differential computer (EDCOM) and a - input of a reference signal with the frequency AMu of the transmitting laser, b - input of a signal from the channel for evaluating the tangential component of velocity (angular velocities) of the aircraft (LA) for clarification of the error of coincidence in the corners, "which differs in that after the SP an information block is additionally introduced, which is connected y with transmitting optics for forming the transmitted information and ECOM for processing the information received from the aircraft, and the 0th with its display. ;" name) (95) name) - 50 syu" with 60 b5