RU2526495C2 - Automated system for measuring radio characteristics of missile homing heads - Google Patents

Abstract

FIELD: physics, navigation.

SUBSTANCE: automated system for measuring radio characteristics of missile homing heads relates to radio measurements and can be used for experimental evaluation of radio characteristics of homing heads having an antenna and a protected radioparent radome. The disclosed system comprises a remote controlled two-dimensional rotary support, having angular position sensors for the radome (heading α and pitch β), a direction-finding antenna of the homing head, measuring antennae (target simulators), measuring devices (for measuring amplitude-phase ratios of signals and relative amplitude values), a generator (source of probing radiation) and a control computer.

EFFECT: high accuracy of estimating direction-finding errors, enabling initial system calibration, taking into account direction-finding errors on an orthogonal coordinate, measuring radio characteristics in the entire scanning sector, high measurement efficiency.

1 cl, 3 dwg

Description

The invention relates to the field of radio engineering measurements and can be used for experimental evaluation of radio technical characteristics (PTX) of homing heads (GOS) containing an antenna protected by a radio-transparent fairing.

To ensure the necessary accuracy of pointing the missile at the target, it is necessary to determine with high accuracy the direction-finding errors introduced by the radiolucent radome, and the change in the transmission coefficient of the signal power at different mutual angular positions of the radio-optical axis of the protected direction finding antenna of the seeker and the construction axis (axis of symmetry, hereinafter, the axis) of the antenna radome .

Known devices for measuring the RTX of a GOS, containing a slewing rotary device (OPU) for mutual movement of the fairing relative to the direction-finding antenna, position sensors of the fairing, auxiliary radiating antennas (target simulators) placed in front of the direction-finding antenna, a source of probing signals supplied to auxiliary antennas (target simulators ) and measuring equipment connected to the total and differential (in course and pitch) outputs of the direction-finding antenna.

Examples are the measuring devices of the inventions SU 459744, RU 2133478, RU 2287834.

Common disadvantages of the known devices is the low accuracy and insufficient completeness of the PTX seeker in the seeker in the scanning sector of the seeker antenna of the seeker.

Closest to the claimed technical solution is the device according to patent RU 2287834С1.

The disadvantages of this device, taken as the closest analogue in relation to the claimed technical solution, are:

1) low accuracy of the estimation of direction-finding errors introduced by the fairing at its various angular positions relative to the direction-finding antenna, due to the use of a combined experimental-calculation method for evaluating the measured characteristics;

2) lack of initial calibration (certification) of the measuring installation;

3) the lack of accounting for direction-finding errors in the orthogonal coordinate (in pitch — when the fairing moves in the direction of the directional plane);

4) the inability to measure PTX in the entire scanning sector;

5) low measurement performance.

The purpose of the claimed solution is to eliminate the disadvantages of the analogue.

The specified goal and the claimed technical result are achieved by the fact that the automated system for measuring the RTX of the GSN contains a remotely controlled two-coordinate control system 1, containing the sensors of the angular position of the fairing along the course "α" and the pitch "β" and ensuring the angular movement of the fairing 2 relative to the fixed direction finding antenna of the GSN 3, on coordinates «α» and «β» within regular scan sector (α ₁ -α _2, β ₁ -β ₂₎ 3 GOS antenna radome axis 2 with respect to the composition of GOS, measuring antenna 4.1 ÷ 4.5 (q simulators Whether) placed in the far field antenna GOS, one of which 4.1 is preset at equisignal direction (PCH) antenna GOS 3, and others (4.2 ÷ 4.4) are arranged in XY plane orthogonal to the original RDA antenna GOS 3 at distances (± L _x1 ) and (+ L _y1 ) from the first of the aforementioned antennas - 4.1 (in both directions - along the course “α” and pitch “β”), equivalent to the maximum values of direction-finding errors “γ _x ” and “γ _y ” on course and pitch to be measured, each measuring antenna 4.1 ÷ 4.5 is connected to the corresponding switched output software-controlled generator 5 - a probe radiation source, the total A _Σ and differential (A _α and A _β ) outputs of the seeker antenna 3 are connected to the corresponding inputs of the measuring devices 6.1 and 6.2, providing measurement of the amplitude-phase ratio of the signals from the outputs of the differential channels of the seeker 3 antenna signals with respect to the total yield of the antenna GOS and 6.3 to a device capable of measuring the relative values of a _Σ signal amplitude _Σ a total yield of GOS antenna 3 with respect to the reference signal amplitude a _op, tvetvlennogo from output A _op generator 5 - source of the probe radiation, the outputs of the sensors α and β OPU 1 and outputs A _α, F _α, A _β, P _β, A _Σ measurement devices 6.1, 6.2 and 6.3 are connected via a bus interface to the control computer 7 measuring system, the control outputs of which are connected to the inputs α and β of the remote-controlled drives of the control gear 1 at the rate “α” and the pitch “β”, as well as to the input of a program-controlled generator 5 (including for controlling the switching of probing signals supplied alternately to measuring antennas 4.1 ÷ 4.5).

The device of the claimed measuring system is illustrated in figure 1, where the corresponding numbers indicate the components of the system listed above, as well as the significant structural relationships between the components, ensuring the implementation of the claimed technical effect.

The claimed measuring system of figure 1 has several modes of operation and several modifications of its technical implementation:

1) calibration mode;

2) PTX measurement mode with fixed measuring antennas (target simulators);

3) PTX measurement mode with a movable measuring antenna;

4) the mode of measurements of PTX at the intermediate frequency of the GOS.

Work in the calibration mode of the measuring system of figure 1 is performed with the cowl 2. removed. Using auxiliary means (for example, a movable tripod with a movable mount of the measuring antenna 4.1), the measuring antenna 4.1 is mounted on the RSN of the direction finding antenna GSN 3 at the rate of "α ₀ " and the pitch " β ₀ ". The installation of the measuring antenna 4.1 is carried out by constantly supplying sensing signals to it from the output of the generator 5 and analyzing the current values of the amplitudes A _α and A _β from the outputs of the difference channels of the direction finding antenna GSN 3, measured using meters of amplitude and phase ratios (hereinafter - AF amplifiers) ( measuring devices 6.1 and 6.2). On the basis of these measurements, when the measuring antenna 4.1 is located on the β β ₀ RSN along the pitch and during the successive movement of this measuring antenna 4.1 along the X coordinate (coplanar directional plane α _i , β ₀ ) to both sides of the α ₀ RSN at the course, the amplitude and phase diagrams of the difference channel of the GSN 3 antenna will be obtained at the course A _a (l _x ) and Ф _α (l _x ), a typical view of which is shown in Fig. 2. The amplitude and phase diagrams A _β (l _y ) and Ф _β (l _y ) will be obtained in a similar way when the measuring antenna 4.1 is constantly located on the RSN at the rate α ₀ and when the measuring antenna 4.1 is moved in the orthogonal direction ± Y coplanar to the pitch plane β _i . The shape of the course and pitch diagrams (with the symmetry of the seeker antenna 3) will be similar to FIG. 2.

The distances (+ l _x ) and (-l _x ) correspond to the extreme points of the linear portion of the phase diagram of FIG. 2 of the difference channel in the heading. Similarly, for pitch we get the distances (+ l _y ) and (-l _y ).

The distance R between the phase center of the direction finding antenna of the seeker 3 and the phase center of the measuring antenna 4.1 should satisfy the conditions of the far zone, i.e. according to the ratio known from antenna technology and antenna measurement technology, the ratio must satisfy the condition:

$$R>\frac{2{\mathrm{<figure-callout\; id="2"\; label="D"\; filenames="00000020.png"\; state="\{\{state\}\}">D</figure-callout>}}^2}{\lambda }\text{(one)}$$

where R is the distance between the phase center of the direction finding antenna of the seeker 3 and the phase center of the measuring antenna 4.1 (the plane of the phase centers of the measuring antennas 4 - with several antennas in the system);

D is the maximum aperture size of the aperture of the seeker antenna 3;

λ is the radiation wavelength at which the GOS operates.

Based on the known distance R between the phase centers of the GSN 3 direction-finding antenna and the measuring antenna 4.1, the deviations from the RSN are (± l _x1 ) at the rate n by the (± l _y1 ) value at the pitch when measuring the calibration diagrams of FIG. 2 at the rate (similar to - pitch) correspond to the angular deviations of the bearing line from the RSN by the values (± γ _α1 ) and (± γ _β1 ), determined by the known trigonometric relations:

$$\{\begin{array}{c}{\gamma }_{\alpha \mathrm{one}}=arctg\frac{l_{x\mathrm{one}}}{R};\\ {\gamma }_{\beta \mathrm{one}}=arctg\frac{l_{y\mathrm{one}}}{R}.\end{array}\text{(2)}$$

From relations (2) it follows that if the expected maximum values of direction-finding errors (γ _αmax ) or (γ _βmax ) introduced by the cowl 2 do not exceed the values γ _α1 and γ _β1 in relation (2), then as a part of the measuring system it is not necessary to use additional measuring antennas 4.2 and 4.3 in the X coordinate or 4.4 and 4.5 in the Y coordinate, respectively.

If the expected values of direction finding errors (γ _αmax ) or (γ _βmax ) exceed the values obtained by relation (2) based on the calibration amplitude and phase diagrams of the difference channels of Fig. 2, then additional measuring antennas 4 must be installed in the corresponding scanning directions of the fairing 2.

The number of additional measuring antennas, which must be placed in this case on each side of the main measuring antenna 4.1, will be determined by the maximum value of the measured direction finding error at the heading and pitch, respectively. The ratio for selecting the number of additional measuring antennas in the direction in the direction (± X) (similarly, in pitch in the Y direction) will be:

$$n(+x)=n(-x)\ge \frac{{\gamma }_{\alpha \max }-0.5{\gamma }_{\alpha \mathrm{one}}}{{\gamma }_{\alpha \mathrm{one}}};\text{(3)}$$

where γ _α1 is the angular width of the amplitude diagram of the difference channel of figure 2, corresponding to the linear portion of the phase diagram of the same channel;

n (+ x), n (-x) - the number of additional measuring antennas located on both sides of the main measuring antenna 4.1 (integers).

The calibration amplitude and phase diagrams of the difference channels according to the course and pitch of Fig. 2, obtained in this way, are entered into the memory of the control computer 7 in the form of tables:

$$\{\begin{array}{c}{\gamma }_{\alpha }=f_{\alpha }(U_{\alpha },F_{\alpha });\\ {\gamma }_{\beta }=f_{\beta }(U_{\beta },F_{\beta }).\end{array}\text{(four)}$$

The advantage of such tables is that (depending on the implemented accuracy of measuring the amplitude (U _α , U _β ) and phase (Ф _α , Ф _β ) ratios of the signals at the output of the difference channels) the determination of direction-finding errors can be made on the basis of amplitude and phase or based only on phase diagrams of difference channels of FIG. 2. In the first case, the basis is the amplitude diagram γ _α (U _α ), and the phase diagram is only used to determine the direction of displacement of the bearing line (plus Ф _α or minus Ф _α ).

по диаграммам фиг.2 (на основе измеренных значений U_αi и Ф_αi), а после этого измерительная антенна 4.1 указанным ранее способом перемещается в результирующее положение РСН l_xi. На основе соотношения (2) определяется фактическое значение пеленгационной ошибки $${\gamma }_{\alpha i}^{П}$$

, которое сравнивается с расчетным значением $${\gamma }_{\alpha i}^p$$

, полученным на основе калибровочных амплитудно-фазовых диаграмм (4). Разность этих значений будет определять методическую погрешность Δγ измерений при неподвижных измерительных антеннах 4:If it is necessary to further improve the accuracy, an additional calibration of the amplitude-phase diagrams of the difference channels of Fig. 2 can be made when the cowl is worn. In this case, after installing the fairing 2 on the control panel 1, for several angular positions α _{i of the} fairing 2, the value of the direction finding error is estimated $${\gamma }_{\alpha i}^p$$

according to the diagrams of Fig. 2 (based on the measured values of U _αi and Ф _αi ), and after that the measuring antenna 4.1 is moved in the previously specified way to the resulting position of the PCN l _xi . Based on relation (2), the actual value of the direction finding error is determined $${\gamma }_{\alpha i}^P$$

which is compared with the calculated value $${\gamma }_{\alpha i}^p$$

obtained on the basis of calibration amplitude-phase diagrams (4). The difference between these values will determine the methodological error Δγ of measurements with stationary measuring antennas 4:

$$\Delta \gamma \alpha =|\; |\; |{\gamma }_{\alpha w}^s-{\gamma }_{\alpha i}^P|\; |\; |;\text{(5)}$$

where Δγα is the value of the measurement error by the method of stationary measuring antennas;

- значение пеленгационной ошибки, полученное для положения обтекателя «α_i» на основе калибровочных диаграмм (4); $${\gamma }_{\alpha i}^p$$

- the value of the bearing error obtained for the position of the fairing "α _i " on the basis of calibration diagrams (4);

- значение пеленгационной ошибки для того же положения обтекателя, $${\gamma }_{\alpha i}^P$$

- the value of the direction finding error for the same position of the fairing,

obtained by moving the measuring antenna 4.1 to the resulting RSN (direct method).

The operation of the measuring system in the measurement mode of direction-finding errors and transmission coefficient with stationary measuring antennas is as follows.

According to the results of the calibration, in the memory of the control computer 7, calibration dependences of direction-finding errors on the values of the amplitude and phase in the difference channels are formed, as well as the dependences of the amplitude diagram of the total channel at angular displacements on the initial direction of the bearing:

$$\{\begin{array}{c}{\gamma }_{\alpha }=f_{\alpha }(U_{\alpha },F_{\alpha });\\ {\gamma }_{\beta }=f_{\beta }(U_{\beta },F_{\beta });\\ U_{{\displaystyle \sum \alpha }}=f_{\mathrm{one}}({\gamma }_{\alpha });\\ U_{{\displaystyle \sum \beta }}=f_{\mathrm{one}}({\gamma }_{\beta });\end{array}\text{(6)}$$

where уα and уβ are calibration tables (4);

, $$U_{{\displaystyle \sum \beta }}$$

- относительные значения амплитуд сигналов на выходе суммарного канала, полученные при смещениях измерительной антенны 4.1 по X и Y, соответственно (синхронно с измерениями диаграмм фиг.2). $$U_{{\displaystyle \sum \alpha }}$$

, $$U_{{\displaystyle \sum \beta }}$$

- the relative values of the amplitudes of the signals at the output of the total channel obtained at the displacements of the measuring antenna 4.1 in X and Y, respectively (synchronously with the measurements of the diagrams of figure 2).

In the initial state, the main measuring antenna 4.1 is located on the RSN of the GSN 3 direction-finding antenna and is permanently fixed. The required number of other measuring antennas 4.i is installed on both sides of the main measuring antenna 4.1 at distances from its phase center (± l _xi ) and (± l _yi ), determined from relation (3):

$$\{\begin{array}{c}{l}_{xi}=n_i\cdot R\cdot [tg({\gamma }_{\alpha \mathrm{one}})]\\ l_{yi}=n_j\cdot R\cdot [tg({\gamma }_{\beta \mathrm{one}})]\end{array}\text{(7)}$$

where l _xi , l _yi is the distance between the phase center of the main measuring antenna 4.1 and the phase centers of the subsequent numbers “n _i ” and “n _j ” of the additional measuring antennas according to the coordinates “X” and “Y”, the number of which is determined by the relation (3) .

Upon completion of the calibration of the measuring system on the OPU 1 fairing 2 is installed and the measurement cycle begins, including:

1) a reference to the current position (α _i , β _j ) of the fairing 2 at the heading and pitch relative to the initial RSN “α ₀ β ₀ ” of the direction finding antenna of the seeker 3. The value of the current coordinates (α _i , β _j ) is determined using the angular position sensors “α "And" β "that are part of the OPU 1.

Codes of coordinate values (α _i , β _j ) via the interface buses enter the control computer 7, which automatically controls the movement of the fairing 2 using remotely controlled drives of the control gear. At the same time, in order to avoid damage to the fairing, for each current coordinate value of the position of the fairing by pitch (β _i ), the control computer 7 controls the maximum permissible values [α _max (β _j )] of the position of the fairing according to the course determined by the boundaries of the scanning sector of the fairing 2 relative to the GPS 3 antenna ( the design of the "antenna-fairing" GOS). Until the resulting position of the PCN is outside the limits (± γ _α1 , ± γ _β1 ) determined on the basis of the calibration tables (6) and relation (2) for the main measuring antenna 4.1, the probing signals from the output of the generator 5 are fed to the input measuring antenna 4.1. When the value of the direction finding error γ _α or γ _β increases outside the measurement zone using the main measuring antenna, the probing signals begin to be fed from the output of the generator 5 to the next additional measuring antenna. For each current position of the fairing 2 (α _i , β _j ), the amplitude and phase relations (U _α , Ф _α, U _β , Ф _β ) of the signals from the outputs of the differential channels of the GPS 3 antenna, as well as the amplitude ratios from the output of the total antenna channel, are measured 3. The codes of these values from the outputs of the corresponding measuring devices 6.1, 6.2, 6.3 enter the control computer 7, where the current values of direction-finding errors, the steepness of direction-finding errors (KPO) for each coordinate and the current value of the transmission coefficient Atelier.

The current values of direction-finding errors γ _α and γ _{β are} determined based on the measured values (U _α , Ф _α ) and (U _β , Ф _β ) using the calibration tables (6). When the value of the direction-finding error falls outside the measurement zone of the main measuring antenna 4.1, the computer automatically adds the correction for the position number (n _i ) or (n _j ) of the additional measuring antenna arising from the initial value of the direction-finding error obtained from the initial calibration table (6) relations (7). The determination of the passage coefficient of the fairing in amplitude is carried out by dividing the current value of U _Σ (α _i , β _j ) by the calibration values of U _Σ from the calibration table (6) in the memory of the control computer.

Measurement cycles are repeated after the installation of the fairing 2 with the help of the control panel 1 under the control of the computer 7 in the next angular position β _{j + 1} in pitch and the movement of the fairing 2 along the coordinate α (at the heading) within the scanning sector acceptable for the given angular position β _{j + 1} in pitch. Measurements are completely completed after passing all course sections within the pitch scanning sector. As a result of this, an array of values of the basic direction-finding error γ _α (α, β) and the orthogonal component γ _β (α, β) of the direction-finding errors introduced by the fairing at different angular positions relative to the radio-optical axis of the GSN 3 antenna will be obtained in the computer at the same time. an array of values of the transmission coefficient T (a, p) of the signals for different relative positions of the fairing 2 and the antenna of the seeker 3 in the scanning sector (α ₁ -α ₂ ) × (β ₁ -β ₂ ). If it is necessary to more accurately estimate the vector values of direction-finding errors, the GSN 3 direction-finding antenna can be reinstalled on the control board 1 with a 90 ° turn. The position of the directional and pitch planes will change in this case, the full measurement cycle of the PTX GSN will be repeated for the new position of the antenna of the GSN 3.

The considered measurement method using the system of Fig. 1 allows to achieve higher accuracy in estimating direction-finding errors, KPO values (continuously calculated in the computer as the cowl moves along the α and β coordinates) and transmission coefficient - in comparison with the closest analogue.

Reliable primary calibration (certification) of the measuring system is provided, the metrological characteristics of which are directly determined by the measuring instruments that make up the system. The completeness of the estimation of the RTH characteristics of the seeker is ensured in the entire scanning sector of the antenna of the seeker 3 relative to the fairing 2. Thus, the claimed technical result, which consists in ensuring the reliability of measurements by initial calibration, improving the accuracy and completeness of the assessment of the RTH values of the seeker is achieved.

However, the considered method does not allow to reach the extreme accuracy of estimating the RTX of the GOS due to the presence of methodological errors (5) associated with the determination of the PTX values from the calibration tables, which are based on the amplitude and phase diagrams of the difference channels of Fig. 2 of the GOS antenna 3. In this method, the measurement errors amplitude and phase relationships are involved twice (during calibration and during measurements), which increases the resulting error in the PTX estimation (although it will be less than that of the analogue). In this regard, a modification of the measuring system of FIG. 1 is proposed, in which additional measuring antennas are excluded, the main measuring antenna 4.1 is mounted on a controlled coordinate device with the possibility of simultaneous movement in the “X” and “Y” directions under the control of computer 7, and PTX measurements are made in the mode of a movable measuring antenna 4.1.

Operation of the system in the measurement mode of the RTX GOS with a movable measuring antenna

Consider the operation of the modification of the measuring system of Fig. 3, in which additional measuring antennas are excluded, the measuring antenna 4.1 is mounted on a remotely controlled two-coordinate device 8. The measuring antenna 4.1 is moved along the coordinates “X” and “Y” in the plane perpendicular to the RSN of the DOS antenna 3 in the absence of a fairing (as in the initial calibration according to the previously considered measurement method with a stationary measuring antenna). The current position of the measuring antenna 4.1 in the displacement plane is measured using the corresponding displacement sensors "l _x " and "l _y " included in the coordinate device 8. The codes of the current coordinates (l _xi , l _yj ) of the measuring antenna 4.1 are received from the sensors of the coordinate device 8 through the interface bus to a control computer 7. The control computer C 7 control output actuators for actuating the coordinate (l _x, l _y) coordinate device 8 through the interface bus are supplied commands (L _xi, L _yj) for SET 4.1 Application of the measurement antenna in the antenna current position PCH GEOSS.

The method of measuring the RTX of the GOS using the system of figure 1 using a modification of this measuring system according to figure 3 is as follows.

Before starting the measurements, with the cowl 2 removed and the GSN 3 direction-finding antenna stationary, the measuring antenna 4.1 is controlled to move along the “X” and “Y” coordinates (similar to the calibration procedure of the measuring system of FIG. 1) to install the measuring antenna 4.1 exactly in the RSN position (see figure 2) corresponding to the original coordinates (l _x0 , l _y0 ). In this position, the current values of the phase difference (Φ _α0 ) and (Φ _β0 ) are measured at the outputs of the difference channels "α" and "β" of the GSN direction-finding antenna 3. The codes of these values are recorded in the memory of the control computer 7 as basic (reference, reference) values. At the same time, the initial value of the relative amplitude level U _Σ is recorded at the output of the total channel of the GPS 3 antenna. At this point, the initial calibration procedure and preparing the system of Fig. 3 for measurements are completed.

) и (Ф_β0) в данном способе несущественны. Важна стабильность и повторяемость показаний фазоизмерительных каналов, а особенно - минимальная разрешающая способность по измерению значений разности фаз (dФ_α) и (dФ_β).It should be noted that the errors of measurement of phase differences ( $$F_{{\alpha }_0}$$

) and (Ф _β0 ) in this method are not significant. The stability and repeatability of the readings of the phase measuring channels is important, and especially the minimum resolution for measuring the values of the phase difference (dF _α ) and (dF _β ).

The procedure for subsequent measurements of the RTX of the GOS, as for the previously considered version of the system of Fig. 1, is based on the cyclic movement of the cowl 2 installed on the control panel 1 along the coordinate "α" (course) with periodic resetting of the position of the control panel 1 to the next coordinate value "β _j " ( pitch) and control over the location of the fairing in the valid scanning sector. Due to the influence of the fairing, the resulting position of the RSN of the GSN 3 antenna will shift along the coordinates “X” and “Y” in the plane of movement of the measuring antenna 4.1 on the coordinate device 8. The shift of the position of the RSN leads to a change in the sign and value of the phase difference (Ф _α ) and (Ф _β ) at the outputs of the corresponding differential channels of the seeker antenna 3. The value and sign of the phase difference codes (Ф _α ) and (Ф _β ) will signal the magnitude and direction of the displacement of the resulting position of the RSN of the seeker 3 relative to the initial position of the RSN (l _x0 ) and (l _y0) for antenna CH 3 without shroud 2 (i.e., the magnitude and sign of the direction-finding errors introduced by the fairing 2).

The control computer 7 analyzes the codes of the current values (Ф _α ) and (Ф _β ) coming from the outputs of the measuring devices 6.1 and 6.2. If the current values deviate from the initial values (Ф _α0 ) and (Ф _β0 ) established during the calibration of the measuring system and corresponding to the location of the measuring antenna 4.1 on the PCH, the control computer 7 generates control commands to the coordinate device 8. According to these commands, the measuring antenna 4.1 moves from position (l _x0 ) and (l _y0 ) to the new position (l _xi ) and (l _yj ), corresponding to the new position of the RSN (due to direction-finding errors introduced by the cowl 2 when it moves relative to the seeker antenna 3). The current values of the coordinates (l _xi ) and (l _yj ) are measured using the sensors included in the coordinate device 8. The control computer 7 determines the difference between the current values of the coordinates and the initial values of the coordinates of the position of the measuring antenna 4.1:

$$\{\begin{array}{c}\Delta l_{xi}=(l_{xi}-l_{x0});\\ \Delta l_{yj}=(l_{yj}-l_{y0}).\end{array}\text{(8)}$$

Based on the measured linear deviations (Δl _xi and Δl _yj ) of the position of the measuring antenna 4.1 (corresponding to the angular deviations of the resulting position of the RSN of the seeker 3 due to the movement of the cowl 2 along the coordinates "α" and "β"), the control computer 7 determines (2) current values of direction-finding errors γ _α (α _i , β _j ) and γ _β (α _i , β _j ). To ensure the required accuracy, the control computer 7 coordinates (regulates) the speed of movement of the control gear 1 (scanning speed of the fairing 2 relative to the antenna of the GOS 3) and the speed of movement of the measuring antenna 4.1 at the coordinates “X” and “Y” on the coordinate device 8 so that the current values the phase differences Ф _α and Ф _β did not exceed the values limited by the permissible measurement error of the RTX of the GOS. In the extreme case, these deviations should not exceed the resolution of the phase difference meters of devices 6.1 and 6.2 (quantization intervals of the measured values of the phase differences “dF _α ” and “dF _β ”).

The speed of moving the control gear 1 along the coordinate “α” (when scanning a sector with sections β _j ) is controlled in a control computer based on a continuous calculation of the value of KPO by the ratio

$$\mathrm{TO}P\mathrm{ABOUT}=\frac{{\gamma }_{i+\mathrm{one}}-{\gamma }_i}{{\alpha }_{i+\mathrm{one}}-{\alpha }_i}=\frac{\Delta {\gamma }_{i+\mathrm{one}}}{d\alpha };\text{(9)}$$

where dα is the interval along the coordinate "α", on which the current values of the KPO are determined;

Δγ _{i + 1} - the current change in the value of the bearing error y when moving the fairing by the value of "dα".

Similarly, the KPO value is controlled by the orthogonal component (along coordinate β).

и $${Ф}_{{\beta }_0}$$

для каждого значения координат (α_i, β_j) с помощью измерительного устройства 6.3 производится отсчет текущего значения амплитуды сигнала с выхода суммарного канала U_Σ(α_i, β_j). На основе этого значения, поступающего в управляющей компьютер 7, и на основе исходного значения $$U_{{\displaystyle \sum 0}}$$

(полученного при калибровке измерительной системы для снятого обтекателя 2 и при нахождении измерительной антенны 4.1 в положении РСН на координатном устройстве 8) определяются текущие значения коэффициента прохождения обтекателя Т по амплитуде:Simultaneously with monitoring the current values of the phase difference $$F_{{\alpha }_0}$$

and $$F_{{\beta }_0}$$

for each coordinate value (α _i , β _j ) using a measuring device 6.3, the current value of the signal amplitude from the output of the total channel U _Σ (α _i , β _j ) is counted. Based on this value received in the control computer 7, and based on the initial value $$U_{{\displaystyle \sum 0}}$$

(obtained when calibrating the measuring system for the removed cowl 2 and when the measuring antenna 4.1 is in the PCH position on the coordinate device 8), the current values of the passage coefficient of the cowling T in amplitude are determined:

$$T_U({\alpha }_i,{\beta }_j)=\frac{U_{{\displaystyle \sum }}({\alpha }_i,{\beta }_j)}{U_{{\displaystyle \sum 0}}}.\text{(10)}$$

Thus, when using a movable measuring antenna 4.1, moved under the control of a computer 7 using a coordinate device 8, in the modification of the measuring system of FIG. 3, higher measurement accuracy is achieved compared to the closest analogue and the measuring system of FIG. 1 with a stationary measuring antenna 4.1. This ensures the necessary completeness of measurements of the RTX of the GOS in the entire sector of relative movements of the fairing 2 and the antenna of the GOS 3 along the coordinate "α, β".

The measurement mode of the RTX GOS at an intermediate frequency is used when the measuring devices 6.1, 6.2 and 6.3, when measuring at the frequency of the probing signals f, do not have the necessary sensitivity or when a reliable assessment of the PTX values using standard stages of frequency conversion and amplification at the intermediate frequency F is required _P from the composition of the GOS. To implement this mode as a part of the measuring systems of FIG. 1 and FIG. 3, respectively, the generator 5 is made in the form of a frequency synthesizer having an output at the frequency of the probing signals f ₁ connected to a measuring antenna 4.1 (as well as to additional measuring antennas 4 in the embodiment system 1), the output signal of the local oscillator f ₂ supplied to the mixers of the total and differential channels as part of the standard antenna GOS 3, and the output of the reference signal at an intermediate frequency F _P supplied to the input of the meter of the amplitude of the total channel (measure device 6.3). As measuring devices 6.1, 6.2, and 6.3, in this case, amplitude and phase difference meters are used, similar in function to the previously considered applications of the measuring systems of Fig. 1 and Fig. 3, but connected to the outputs of the standard intermediate frequency amplification cascades (IF) from the structure of the standard antenna of the seeker 3 and measuring the amplitude-phase ratio of the signals from the outputs of the differential and total channels of the antenna of the seeker 3 at an intermediate frequency F _P.

In all other respects, the implementation of measurements in modifications of the measuring systems of FIG. 1 and FIG. 2, using measurements of amplitude and phase signals at an intermediate frequency F _P , is similar to the previously discussed methods for measuring RTX of a GOS using a fixed and mobile measuring antenna 4.1, respectively.

The technical implementation of the claimed variants of the measuring system is carried out on the basis of devices known from the prior art. As the OPU, a device identical to the same devices from the analogues is used. As measuring devices for measuring the amplitude and phase ratios, serial digital measuring instruments (ampliphase meters, signal vector meters), produced by domestic and foreign industry, are used. As generators, serial programmable generators of domestic and foreign production are used for the corresponding frequency ranges of the GOS operation (including the frequency synthesizer circuit). As a control computer, a serial personal computer of domestic or foreign production is used. The coordinate device is implemented on the basis of structural solutions known from the prior art since the 70s of the last century (for example, equipment from Signtific Atlanta, USA, California). The movement control vertically and horizontally in the coordinate device 8 can be carried out using high-speed helical gears connected to stepper motors. The readings of the OPU positions and the positions of the measuring antenna on the coordinate device are carried out using serial encoder displacement sensors of domestic or foreign production, which have the necessary accuracy.

The claimed measuring system and its modifications can be used in experimental testing of GOS at the stage of development of prototypes, in serial production of GOS and antenna fairings, as well as in monitoring the technical condition of GOS at repair enterprises and service centers.

Claims (3)

1. An automated system for measuring the radio technical characteristics of missile homing heads (hereinafter referred to as the system), including a standard homing antenna (hereinafter referred to as the GPS antenna), a rotary support device (OPU), which allows the installation and controlled movement of the measured radio transparent radar antenna of the GSN (hereinafter referred to as the antenna) - fairing) along two orthogonal coordinates, a measuring antenna located in the far zone of the GSN antenna, a probe signal generator, the output of which is connected to the measuring antenna, In that the rotary support device includes displacement sensors and remotely controlled drives for each coordinate of the fairing movement (in the course and pitch) relative to the fixed seeker antenna, the system additionally incorporates meters of the amplitude and phase ratios of the signals from the outputs of the differential channels of the seeker relative to the total channel of the seeker antenna, measuring inputs connected to the outputs of the differential channels of the seeker antenna at the heading and pitch, and the reference inputs connected to the output of the total the antenna of the GOS, a measuring instrument of relative values of the amplitude of the signals, a measuring input connected to the output of the total channel of the antenna of the GOS, and a reference input connected to the output of the reference signal of the probe signal generator, a control computer, to the inputs of which the outputs of the meters of the amplitude-phase relations of the difference signals are connected channels of the GOS antenna and a meter of relative values of the amplitude of the signals of the total channel of the GOS antenna, as well as the outputs of the OPU position sensors at the heading pitch, and the control outputs of the computer through the interface buses are connected to the inputs of the remotely controlled drives of the control gear at the heading and pitch, as well as the control input of the probe signal generator, and before starting the measurements, calibration tables of amplitude-phase diagrams of difference channels of the GOS antenna are entered into the memory of the control computer the absence of a fairing, designed to determine the measured values of the radio technical characteristics at different positions of the fairing relative to the seeker antenna. 2. The system according to claim 1, characterized in that it additionally introduces a coordinate device containing remotely controlled drives for moving the measuring antenna along the “X” and “Y” coordinates in a plane perpendicular to the equal signal direction of the differential channels of the GOS antenna with the cowl removed, and position sensors of the measuring antenna along the coordinates “X” and “Y”, the inputs of the remotely controlled drives and the outputs of the sensors of the position of the measuring antenna are connected via interface buses to the corresponding outputs and inputs of the control unit computer, the measuring antenna is mounted on a coordinate device with the ability to move in the “XY” plane so that its initial position ( l _xo , l _yo ) before the measurement starts corresponds to the position of the directional directional antenna of the seeker with the cowl removed, and the current coordinate values ( l _xi , l _yi ) the positions of the measuring antenna correspond to the measured values of direction-finding errors for the current angular position (α _i , β _i ) of the fairing relative to the seeker antenna. 3. The system according to claim 1 or 2, characterized in that when using a GOS antenna containing standard mixers and amplifiers of the intermediate frequency of the differential channels in the course and pitch and the total channel, a meter of the amplitude-phase ratios of the difference channels in the course and pitch, as well the meter of the amplitude ratios of the total channel, operate at an intermediate frequency and are connected to the corresponding outputs of the amplifiers of the intermediate frequency of the differential and total channels of the GOS antenna, as a generator of probing signals enjoy thi s frequency synthesizer, the output of the probing signal which is connected to the measuring antenna, the local oscillator output is connected to the antenna GOS mixers, and the reference signal at the intermediate frequency output connected to the input of the reference signal measuring amplitude ratios of the total channel.

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