RU209899U1 - A device for determining the corrections of installations for a multiple launch rocket system - Google Patents

Abstract

The utility model relates to computer technology and can be used to determine the aiming angles of multiple launch rocket systems (MLRS) in the process of aiming with unguided rockets (PC). both high-explosive and cluster projectiles and a wind circle that replaces the Sin and Cos tables to determine the correction for the longitudinal and lateral components of the ballistic wind speed, while the calculator is made on the basis of a slide rule, with additional correction scales applied, calculated using an approximation of the flight path of a rocket projectile curves of a higher order, and the determination of the corrections is carried out by manipulating the engine and the ruler's sight, while each calculator to determine the topographic range of the directional angle of the direction of fire αt, calculate the values of the installation of the sight a Pi, tubes Type Designed for its range of firing range without a brake ring, with a small brake ring and a large brake ring, and the wind circle is made in the form of two coaxial discs of different diameters, and on the lower opaque disc there is a scale of wind direction angles, and on a smaller one, the upper transparent disk contains a mark of the wind speed value, while the wind speed components are counted along the X and Z axes by turning the wind mark point on the rotating transparent circle by the directional wind angle, and the longitudinal and lateral wind components are determined as the corresponding projections on the X and Za axes, and calculators for each range of firing both high-explosive and cluster shells differ from each other by marking additional scales.

Description

The utility model relates to computer technology and can be used to determine the aiming angles of multiple launch rocket systems (MLRS) in the process of aiming. Unguided rockets (PC) are used as ammunition. The claimed utility model allows you to determine the corrections for the initial installation angle of the sight and the directional angle corresponding to the estimated range and direction to the target, from the influence of such disturbing factors as pressure deviation ΔΗ, air temperature deviation ΔΤ _in , jet engine charge temperature deviation ΔT _z , speed W and wind direction α _w .

A computing device for firing is known (US patent No. 3739153, IPC G06G 7/80), containing a handset, buttons, relays, scales for entering information using potentiometers. Calculating device by target coordinates provides information on the dependence of the aiming angle on the topographic distance to the target, which is read visually from the scales of potentiometers.

The disadvantages of the known computing device are: visual reading of information from the scales of potentiometers, the analog principle of operation of the computing device of the electromechanical type, and as a result, low accuracy, as well as relatively low speed. In addition, this computing device does not allow to determine corrections for installations for the deviation of air temperature, temperature of the charge of the engine, tube, wind speed and direction.

Also known are TS-84RG - Tables for firing 220-mm rockets 9M27F and 9M27K lowland-mountain. - M.: Military publishing house 1988 - 272 s, recommended for preparing data for firing MLRS. In the Tables, the parabolic trajectory of the flight of rockets, the points of which are analytically calculated by integration, is represented by a piecewise linear approximation.

The disadvantages include the description of the flight trajectory by linear functions in the course of piecewise linear approximation, which leads to an increase in the error in determining the corrections for the aiming angles when preparing the MLRS for firing. The large volume of the Tables increases the time required to find corrections that compensate for the effect of the listed disturbing factors, which increases the time for preparing data for firing, and reduces the effectiveness of the combat use of MLRS. In addition, using the Tables it is impossible to determine the topographic range and directional angle.

The technical objective of the utility model is to increase the effectiveness of the combat use of MLRS by increasing the accuracy of calculations and reducing the time required to determine amendments to MLRS installations.

The technical result consists in the use in calculations of the approximation of the flight path PC by higher-order curves using a calculator, which increases the accuracy and reduces the time for determining corrections to MLRS guidance installations due to a significant reduction in manipulations in calculations, as well as using the wind circle to determine the correction of the longitudinal and lateral components wind.

The utility model is illustrated by drawings.

Fig. 1 - General view of the calculator (LRP), where 1 - line sight; 2 - LRP base; 3 - LRP engine.

Fig. 2 - LRP scales of the front side of the engine.

Fig. 3 - LRP scales on the reverse side of the engine.

Fig. 4 - The wind circle of the correction calculation instrument (PRP), where 1 - the line of the wind speed mark; 2 - upper transparent circle; 3 - the lower circle with the applied scale of angles (thousandths).

и угла ρ.Fig. 5 - The procedure for determining the topographic range

and angle ρ.

Fig.6 - The procedure for determining the components of the wind W _x , and W _z , where a) action 1; b) action 2

Fig. 7 - The procedure for taking into account disturbing factors when determining the calculated installation of the sight P _and .

Fig. 8 - The procedure for determining the calculated value of the opening time setting T _and .

Fig. 9 - The procedure for determining the calculated value of the directional angle α _and .

дирекционного угла направления стрельбы α_т, расчета исчисленных значений установки прицела П_и и времени трубки Т_и и дирекционного угла α_и. Каждая ЛРП определяет поправки для своего диапазона дальности стрельбы, первая - без тормозного кольца, для дальности стрельбы 22-35 км; вторая - PC с малым тормозным кольцом, для дальности стрельбы 11-22 км, третья - PC с большим тормозным кольцом для дальности стрельбы 9-15 км. ЛРП разных диапазонов отличаются друг от друга только разметкой нанесенных на них дополнительных шкал. Круг ветра предназначен для определения продольной и боковой составляющей скорости ветра. Отсчеты по осям X и Ζ выполняют поворотом точки отметки скорости ветра на вращающемся прозрачном круге на дирекционный угол, который предварительно определяется на ЛРП, а продольная и боковая составляющие ветра определяются как соответствующие проекции на оси X и Ζ соответственно. По аналогичной методике определяют составляющие ветра на участке полета боевых элементов (УПБЭ) W_ЭX и W_ЭZ. Расчеты по ЛРП не требуют обращения к другим документам и поиска каких-либо справочных параметров, поэтому время определения поправок значительно уменьшается.The technical problem is solved, and the technical result is achieved by the fact that the claimed device (PRP) contains calculators for calculating corrections (LRP), made on the basis of slide rulers for each firing range of both high-explosive and cluster projectiles, differing from each other in the marking of additional scales and wind circle (KW) replacing the Sin and Cos tables. The calculation of corrections is carried out by manipulating the slider and the line sight. Each LRP is designed to determine the topographic range

directional angle of the direction of fire α _t , calculation of the calculated values of the installation of the sight P _and and tube time T _and and directional angle α _and . Each LRP determines corrections for its range of firing range, the first - without a brake ring, for a firing range of 22-35 km; the second - PC with a small brake ring, for a firing range of 11-22 km, the third - PC with a large brake ring for a firing range of 9-15 km. LRS of different ranges differ from each other only by the marking of additional scales applied to them. The wind circle is designed to determine the longitudinal and lateral components of the wind speed. Readings along the X and Z axes are performed by turning the wind speed mark point on a rotating transparent circle by a directional angle, which is previously determined on the LRP, and the longitudinal and lateral components of the wind are determined as the corresponding projections on the X and Z axes, respectively. Using a similar technique, the wind components are determined in the flight section of combat elements (UPBE) W _EX and W _EZ . LRS calculations do not require access to other documents and the search for any reference parameters, so the time for determining corrections is significantly reduced.

Due to the presence of these features, the proposed PRP reduces the error in determining corrections to the guidance installations of combat vehicles, and also reduces the time for preparing parameters for firing MLRS after receiving target designation, which leads to an increase in the combat effectiveness of MLRS.

The novelty of the utility model is that:

- the calculation of additional scales printed on the LRS is based on a new principle that reduces the determination of the flight path of a rocket to a calculation by calculating the sum of a converging geometric progression - approximation by higher order curves. The error of such a calculation is equal to the value of the residual term of a geometric progression and tends to zero;

- a new principle for calculating corrections reduces the dispersion ellipse PC with a flat flight path, reduces the consumption of ammunition, brings multiple rocket launchers closer to high-precision weapons for destroying area targets;

- all LRS scales are compact and accessible, the calculation does not require recording intermediate results, the addition of corrections is carried out by moving the LRS sight, so it does not take much time to determine all the necessary corrections, while the procedure for searching for the necessary TS-84RG tables in and selecting from them required corrections, up to 30 min. Therefore, the time for determining corrections to settings in preparation for firing is noticeably reduced. Even with little experience of the MLRS operator in the use of LRS, the time for calculating corrections does not exceed 2-3 minutes.

The wide application of the claimed technical solution is possible due to the simplicity of the design of the LRS and the wind circle, their replication and the calculation of corrections with a low error with a small investment of time.

The proposed utility model can compete even with systems for automated calculation of installations.

The utility model contains a calculator and a wind circle. The calculator (Fig. 1, Fig. 2, Fig. 3) is made on the basis of a slide rule, with the application of new, additional scales: range "D", sight "P", atmospheric pressure deviation "ΔΧ _Η ", coordinate difference "Ν "between the batteries and the target, tube time "T". On the front side of the engine (Fig. 2) there are scales of the influence of disturbing factors of the longitudinal component of the wind in the active section of the trajectory "W _A ", the longitudinal component of the wind in the passive section of the trajectory "W _P ", the longitudinal component of the wind in the flight section of combat elements "W _e " , air temperature deviation "ΔТ _В ", charge temperature deviation "ΔТ _З ", as well as "ΔТ _Н " and "Δh". On the reverse side of the LRP engine (Fig. 3), there are standard scales for determining the trigonometric functions "S and T", "tg" and "N".

In FIG. Figure 4 shows the design of the wind circle of the correction calculation instrument, which consists of two coaxially interconnected circles of different diameters, with the upper circle of a smaller diameter made transparent for applying wind speed marks to it during calculations, and the lower circle of a larger diameter made opaque, while on it the scale of angles (thousandths) and the coordinate grid are applied.

The device works as follows.

The initial data for calculating installations for targeting a combat vehicle are the target coordinates (X _C , Y _C , h _C ), battery coordinates (X _B , U _B , h _B ), values of ΔH, ΔT _B , ΔT _W , directional angles and wind speeds α _WP and W _P on the passive section of the trajectory (PUT), α _WЭ , and W _E on the flight section of combat elements (UPBE), α _WA , and W _A on the active section of the trajectory (AUT), and the ultimate goal is to determine the calculated: installation sight P _and , opening time - T _and and directional angle α _and required for targeting a combat vehicle.

и направление стрельбы α_т а по значениям h_ц и h_Б - превышение цели Δh_ц, например,Before calculating them with the help of the LRP, using the coordinates X _c , Y _c and X _B , U _B , by manipulating the engine and the sight on the scales "S and T", "tg" and "N" we determine the range value

and the direction of fire α _t and according to the values h _c and h _B - exceeding the target Δh _c , for example,

Using the circle of the wind, the components W _PX and W PZ are determined on the PUT, W _EX and W _EZ on the _UPBE , W _AX and W _AZ on the OUT.

For example,

α _WP =39-00, W _P =18 m/s - components: W _PX =-15 m/s, W _PZ =-11 m/s.

α _WE \u003d 39-00, W _E \u003d 24 m / s - components: W EX \ _u003d -20 m / s, W EZ \ _u003d -15 m / s.

α _WA =37-00, W _A =17 m/s - components: W _AX =-11 m/s, W _AZ =-14 m/s.

ΔТ _В =30, ΔТ _З =24, ΔН=-90 mm Hg.

The calculated (calculated) data for MLRS guidance, taking into account corrections for disturbing factors, are determined according to the LRP selected for the required firing range, for example, for firing without a brake ring and a range of 24500 m, as follows.

Install the LRP engine face up. On the scale "D" with a sight, set the value

Depending on the sign of the deviation ΔН, we shift the sight to the left (if “-”), or to the right (if “+”), by the value n _Н =0.1⋅ΔН.

на шкале «Д» (фиг.7) визиром на шкале «ΔН» отложим n_Н=0,1⋅ΔН=- 9 делений влево.For example, from the value

on the scale "D" (figure 7) with a sight on the scale "ΔН" set aside n _Н =0.1⋅ΔН=- 9 divisions to the left.

On the scale "W _ПX " with a sight, we set aside n WP \ _u003d 0.1 W _PX \u003d -1.5 cases. left;

On the scale "ΔT _B " with a sight, we set aside n _TV \u003d (0.1⋅ΔΤ _Β ) (-1) \u003d - 3 cases. to the left.

On the scale " ΔT _Z " with a sight, we set aside n _Τ3 \u003d (0.1⋅ΔΤ ₃ ) (-1) \u003d -2.4 divisions. to the left.

On the scale "W _EX ", with a sight, we set aside n _WЭ \u003d 0.1⋅W _EX \u003d -2 cases. to the left

On the “W _AX ” scale, we set aside with a sight n _WA \u003d 0.1⋅W _AX \u003d -1.1 div. to the left.

When performing manipulations, the corrections are algebraically added without recording the intermediate result, and then from the “P” scale we read the value

P _and \u003d 330 thousand,

and on the D scale we get the calculated range D _and = 19400 m.

Similarly (by performing manipulations), manipulations are performed with readings of deviations ΔН, ΔТ _В and ΔТ _З (we set aside with a sight n _Η , n _ΤΒ , n _ТЗ divisions) and we obtain the calculated values of setting the opening time T _and on the "T" scale (Fig. 8).

n _n =- 0.01⋅ΔН=- 0.01⋅(-110)=+1.1 div.

n _TV =0.01⋅ΔΤ _Β =0.01⋅(+30)=+0.3 div.

P _tz \u003d 0.1⋅ΔΤ _Z \u003d 0.1 ⋅ (+24) \u003d + 2.4 divisions.

T _i \u003d 37.2 s.

From the value of D _and \u003d 19400 m on the D scale, similarly in terms of the values W _AZ \u003d -14 m / s, W PZ \ _u003d -11 m / s, W EZ \ _u003d -15 m / s we set aside the corresponding values

n _WПZ =0,l⋅W _Пz =0,l⋅(-11)=-l,l div

n _WЭZ =0.1⋅W _ЕZ =0.1⋅(-15)=-1.5 div.

n _WAZ =-0.1⋅W _AZ =- 0.1⋅(-14)=+1.4 div. and get the range value D and z = ₂₀₄₀₀ m.

After that, we determine the directional angle α _and , according to the formula:

We round the value of the second term to an integer value (40.8≈41) and get

α _and \u003d 1520 + 41 \u003d 1561 thousand,

As a result of these manipulations, according to the obtained initial data, the MLRS installations were calculated:

P _and \u003d 330 thousand,

α _and \u003d 15-61 thousand,

T _i \u003d 37.2 s.

Claims (2)

1. A device for calculating corrections to multiple launch rocket systems, containing at least one calculator for each firing range of both high-explosive and cluster projectiles, and a wind circle that replaces the Sin and Cos tables to determine the correction for the longitudinal and lateral components of the ballistic wind speed, at the same time, the calculator is made on the basis of a slide rule, with additional correction scales applied, calculated using the approximation of the flight path of a rocket projectile with higher-order curves, and the corrections are determined by manipulating the slider and the ruler's sight, with each calculator for determining the topographic range

directional angle of the firing direction α _t , calculation of the installation values of the sight P _and , tube T _and , is designed for its range of firing range without a brake ring, with a small brake ring and a large brake ring, and the wind circle is made in the form of two coaxial disks of different diameters, and on the lower opaque disk there is a scale of wind direction angles, and on a smaller, upper transparent disk there is a mark of the wind speed value, while the components of the wind speeds are counted along the X and Z axes by turning the wind mark point on the rotating transparent circle by the directional wind angle, and the longitudinal and lateral wind components are defined as the corresponding projections on the X and Za axes. 2. A device for calculating corrections to the installations of a multiple launch rocket system according to claim 1, characterized in that the calculators for each firing range of both high-explosive and cluster projectiles differ from each other by marking additional scales.

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