RU2602162C2 - Method of firing jet projectiles multiple artillery rocket system in counter-battery conditions - Google Patents

Abstract

FIELD: military equipment.

SUBSTANCE: invention relates to military equipment and can be used in jet valley fire systems (MARS). Method comprises guiding launcher (L) in horizontal plane in direction of target, lifting guides with rocket missiles (RS) through preset angle starting in vertical plane (VP), estimating time (WS) of flight in system of independent flight path correction (SAKT) PC at initial section of path, including solid rocket engine start is PC at small angle in the IP at initial section of flight trajectory (UTV) PC taking into account technical characteristics of PU and relief arrangement PU, PC is transferred to a new path with large angle in VP after expiry of WS considering conditions of non-detection PC at initial section of trajectory of radar station counter-battery control (CBS) of enemy PC is launched with subsequent according to preset flight ballistic trajectory, simulating start of PC of fictitious point spaced from LS at a safe distance, excluding damage PU enemy artillery fire by results of locating radar station CBS start position MARS controlled pitch and yaw angles PC with help of gas-dynamic rudders by commands from SAKT PC depending on safe flight altitude of PC, which prevents detection by radar CBS, removal of PU from radar station from front line, minimum angle of view of radar station CBS branch of apparent start angle, angle of start PC branch PC speed vector angle corrections to angle of start PC, PC flight speed, permissible overload PC branch of free fall acceleration, hit target.

EFFECT: higher efficiency of firing MARS.

1 cl, 2 dwg

Description

The invention relates to the field of armament, in particular to rockets (PC) multiple launch rocket systems (MLRS), and can be used to provide firing PC MLRS at enemy targets in the conditions of active use of counter-battery weapons.

The MLRS firing process in the general case consists of a series of successive stages: the output of the combat vehicle (BM) at the launch point of the PC; preparation of the launcher (launcher) BM MLRS for launch; PC launch, preparation of BM for leaving and leaving for a new position. The successful completion of the shooting largely depends on the effectiveness of the enemy’s counteraction.

The effectiveness of any methods of firing a MLRS PC depends not only on the type of PC used, the power of their warheads and firing accuracy, but also on the survivability of elements of the MLRS complexes in the conditions of enemy fire reaction. The survivability (operability) of the latter can be impaired as a result of the enemy opening the positions of MLRS units during the shooting and delivering fire strikes at these positions until the RSZO combat vehicles (BMs) leave for reserve positions. Therefore, the task of increasing the effectiveness of the PC MLRS firing at fire counteraction of the enemy (with counter-battery combat) is the most important task of ensuring the effective use of the MLRS during the enemy fire engagement. In this case, the task of increasing the firing efficiency of the PC MLRS in these conditions should be solved, first of all, by using such firing methods that would make it difficult or preclude the enemy from detecting the firing positions of the MLRS and launching artillery attacks on them. In missile troops and artillery, firing methods can be used as such methods, which are based on PC flight paths that mislead the enemy’s counter-battery countermeasures (KBB radar stations).

A known method of firing rockets from launchers of multiple launch rocket systems (patent RU No. 242778, IPC F42B 10/14, 2011). The method is based on loading the PC in the launcher, selecting a specific target (pointing the launcher at the target), the method of hitting that target with single shots, bursts or a single salvo from the launcher and firing directly. The PC is charged in the PU with the blades folded around it by placing them under the transport ring, which is removed when the PC starts up. PC flight after launch occurs along a ballistic trajectory.

The disadvantage of this method of shooting PCs is that when the PC flies towards the target along a ballistic trajectory, they are detected by the enemy’s counter-battery radar (radar) radar stations (RLS), which, after notching the PC trajectory, determine by extrapolating the PC start location (PU position) with an accuracy of several dozens - hundreds of meters (Krupnikov A. radar counter-battery combat of foreign countries. ZVO. 2010. No. 12) and give targeting fire weapons to strike at the position of PU MLRS. Therefore, after starting the PC, launchers placed on the BM are forced to urgently curl up and move to a new position, which significantly increases the execution time of the fire mission and reduces the intensity and density of the fire strike.

There is also a known method of firing rockets of MLRS shells, which consists in pointing the launcher in a horizontal plane in the direction of the target, lifting the guides from the PC to the given angle of launch in the vertical plane (VP), turning on the solid propellant rocket engine, launching the PC with the tail unit open at a given moment for stabilizing the flight of a rotating PC on an estimated ballistic trajectory (Internet ΓΉΠΠ "Fusion" http: //www.splav.arg/ru/arms/uragan/index.asp. Korablin V. Russian SMERCH. Magazine "Arms", No. 9 (20) . - M.: Eastern horizon, 1999, p. 21).

The disadvantages of this method of firing PCs are low firing accuracy due to the influence of both meteorological factors (inhomogeneities of the atmosphere, gusts of wind, etc.) and ballistic firing conditions (installation errors, random nature of the burning speed of solid fuel PC, etc.) and the lack of correction real flight path in accordance with the calculated (ideal) path. Therefore, with this method of firing, PCs are usually launched in one gulp to destroy extended (areal) objects and are ineffective in the conditions of destruction of single objects by a limited number of shells (one or two PCs), which increases the execution time of a fire mission. In addition, with such a firing of the PU position, the enemy’s KBB radar is easily opened, which significantly reduces the survivability of the MLRS launcher.

The closest in essence and the achieved effect is the method of firing a PC MLRS, which consists in pointing the launcher in a horizontal plane in the direction of the target, lifting the guides from the PC to the given angle of launch in the airspace, turning on the solid propellant rocket engine and launching the PC, followed by flight along a predetermined ballistic trajectory , the deviation from which is eliminated by controlling the pitch and yaw angles of the PC with the help of gas-dynamic rudders by commands from the autonomous flight path correction system (SAKT) PC (Reactive system with RELP 9M55 fire "Smerch" Journal "Technology - Youth»., №12, 1992). The deviation of the projectile with this method of firing from the aiming point is only 0.21% of the range, which when firing at 70 km gives a median (probable) range error of the shot equal to 150 m ([Korablin V. Russky SMERCH. Arms magazine, No. 9 (20) .- M .: East Horizon, 1999, p. 19).

However, the main disadvantage of this method is that when the PC is flying toward the target along a ballistic trajectory, they are detected by the enemy’s radar detection system, which, after notching the PC’s trajectory, determines by extrapolation the PC’s launch location (PU position) with an accuracy of several tens to hundreds of meters and gives target designation with fire funds for striking at the position of PU MLRS. Therefore, after starting the PC, launchers placed on the BM are forced to urgently curl up and move to a new position, which reduces firing efficiency, significantly increases the execution time of the fire mission, and reduces the intensity and density of the fire strike.

The technical task of the present invention is to increase the firing efficiency of PC MLRS by providing high survivability of the MLRS launcher in counter-battery conditions by using a trajectory that simulates the launch of the PC from a fictitious point remote from the launcher at a safe distance, eliminating its destruction by enemy artillery fire as a result of notching the starting position MLRS radar field artillery (KBB), while significantly reducing the time to complete a fire mission and increasing the intensity and density of fire on impact, by reducing the number of firing positions shifts.

The problem is solved due to the fact that in the known method of firing a PC, which consists in pointing the launcher in a horizontal plane in the direction of the target, raising the guides from the PC to the given angle of launch in the airspace, turning on the solid propellant rocket engine and launching the PC, followed by the calculated ballistic trajectory, deviation from which is eliminated by controlling the pitch and yaw angles of the PC using gas-dynamic rudders according to commands from SAKT PC, previously before starting the PC along a given ballistic trajectory start the PC first at a small angle in the VP along the initial portion of the flight path (USP) of the PC, after the estimated time of flight PC along the initial portion of the path, the value of which is entered in SAKT before starting the PC, transfer the PC to a new path with a large angle in the VP moreover, the minimum value of the initial launch angle of the PC in the airspace is limited by the technical characteristics of the launcher and the terrain in the area where the launcher is located, and the maximum by the conditions of non-detection of the PC in the initial section of the enemy’s KBB radar trajectory, after which the flight of the PC uschestvlyayut for a given ballistic trajectory to simulate the launch of PC from a fictitious point F, remote from the UE to a safe distance L _without precluding its defeat enemy fire artillery on the results of serifs radar HEC starting position (PU) MLRS, the conjugation of all areas of PC flight path is performed so that the PC, moving along a given ballistic trajectory, falls into the target designated for destruction, and the PC flight path is changed using gas-dynamic rudders according to commands from SAKT, which form in accordance with the required law of the pitch pitch change PC, which provides the initial UTP pairing with the flight path with a large angle in the VP and UTP along the ballistic path, while the values of the PC flight time along the initial UTP t _I and UTP with a large angle in the VP t _{II are} determined by formulas:

,

,

,

,

,

,Where

,

,

H _without - safe flight altitude of the PC, excluding its detection of radar KBB; D _RS , D _radar - removal of PU and radar from the front line (LF), respectively ;.

β is the minimum viewing angle of the radar KBB in the vertical plane (VP);

α _pF is the fictitious launch angle of the PC from point F, at which the flight of the PC along the USP III is ensured;

α _pm is the start angle of the PC in the airspace at which the PC, moving in a straight line, crosses the bottom of the KBB radar at a height of H _without ;

θ is the angle of the velocity vector PC;

Δ is the correction to the start angle of the PC, necessary for pairing the II UTP with I and III UTP PC taking into account permissible PC overloads in the VP;

V, n _y - PC flight speed and allowable PC overload in the airspace, respectively;

g is the acceleration of gravity.

Thus, the proposed method of firing provides an increase in the effectiveness of MLRS, since from a single position on targets a greater number of PCs can be produced than that of the prototype, and at the same time, high survivability of the MLRS can be achieved due to the flight of the PC along trajectories that simulate the launch of the PC from a fictitious point , removed from the launcher at a safe distance, excluding its defeat by enemy artillery fire according to the results of notching the launch position of the MLRS of the enemy’s radar.

The claimed solution has a new property - the ability to deliver effective PC strikes against enemy targets while ensuring high survivability of the MLRS launcher by using such PC flight paths that simulate the launch of the PC from a fictitious point remote from the launcher at a safe distance, eliminating its destruction by artillery fire the enemy according to the results of notching the starting position of the MLRS of the enemy radar. Moreover, the use of the proposed method of shooting can also significantly reduce the time of execution of the firing tasks and increase the intensity and density of the firing strike, by reducing the number of changes of firing positions.

In FIG. 1 shows a structural diagram of a system for implementing the proposed method of firing a PC MLRS in counter-battery conditions. In FIG. 2 is a diagram showing the spatial position of the MLRS launcher, the PC, the target of the target and the enemy’s KBB radar, the parameters characterizing the path of the PC’s launch and flight, the capabilities of the KBB radar to detect PC, and the characteristics necessary to calculate the PC flight time on the PU each USP before starting the PC.

A system that implements the proposed method (Fig. 1) consists of an MLRS launcher 1, a missile 2 and elements placed on them: guides with PC 3, guidance devices PU 1 in the horizontal plane and lifting guides from PC 3 to a given angle in vertical plane 4, calculator of the start time of PC 2, parameters and flight time in various sections of trajectory 5, a device for generating a command to turn on the engine and start of PC 6, a communication device with a control unit with PC 7, a communication device with a PC with control unit 8, a solid propellant rocket engine PC 9 System autonomous correction of the trajectory of PC 10, gas-dynamic rudders of PC 11, as well as from the target-target for PC 12, radar station (radar) counter-battery warfare (KBB) 13, antenna radiation pattern (BOTTOM) radar KBB 14; PC flight paths with a typical firing method 15.

In FIG. 2 is indicated:

F - fictitious launch point PC, determined by the KBB radar;

Ι, ΙΙ, ΙΙΙ - sections of the flight path (USP) of the PC with the proposed method of firing;

I - initial UTP PC with a small angle of start; II - USP PC when switching to a new trajectory that simulates the launch of the PC from point F; III - USP PC along a ballistic trajectory starting at point F; N _without - safe flight altitude of the PC, excluding its detection of radar KBB; L _without - a safe distance from the launcher to the F point at which the launcher’s fire is prevented by enemy artillery fire according to the results of noticing the KBB radar of the launch point PC;

D _RS , D _radar - the removal of PU and radar from the front line (LF), respectively;

β is the minimum viewing angle of the radar KBB in the vertical plane (VP);

α _pF is the fictitious launch angle of the PC from point F, at which the flight of the PC along the USP III is ensured;

α _pm is the start angle of the PC in the airspace at which the PC, moving in a straight line, crosses the bottom of the KBB radar at a height of H _without ;

Δ is the correction to the start angle of the PC, necessary for pairing I and III of the PCS PC with allowable PC overloads in the VP;

Δα is the required angle of rotation of the PC in the VP, at which the transfer of the PC to the USP III is ensured.

Thus, the claimed method of firing PC MLRS allows you to increase the effectiveness of firing MLRS due to the high survivability of the MLRS in counter-battery conditions by using a trajectory that simulates the launch of the PC from a fictitious point remote from the PU at a safe distance, eliminating its destruction by enemy artillery fire according to the results notching the launch position of the MLRS of the KBB radar, while significantly reducing the time it takes to carry out a fire mission and increasing the intensity and density of a fire strike, due to sheniya number of firing positions shifts.

The analysis of the prior art, including a search by patent and scientific and technical sources of information, and identification of sources containing information about analogues of the claimed inventions, allowed us to establish that the applicant did not find any analogues characterized by signs that are identical to all the essential features of the proposed method of firing PC MLRS. The selection from the list of identified analogues of prototypes, as the closest in the aggregate of the essential features of the analogue, allowed to identify a set of new essential in relation to the formulated technical result of the features in the claimed method, which are set forth in the claims. Therefore, the claimed invention meets the criterion of "novelty."

To verify the compliance of the claimed invention with the criterion of "inventive step", a search and analysis of known technical solutions was carried out in order to identify signs that match the features of the proposed method of firing a PC MLRS. The search results showed that the claimed invention does not follow explicitly from the prior art determined by the applicant. The claimed invention does not provide for the following transformations:

supplementing the known means with any known unit attached to it according to known rules to achieve a technical result;

replacing any part of the known means with another known part to achieve a technical result;

the increase in the same type of elements to achieve the formulated technical result;

the creation of a tool consisting of known parts, the choice of which and the relationship between them are carried out according to well-known rules, and the technical result achieved in this case is due only to the known properties of the parts of this tool and the relationships between them.

Therefore, the claimed invention meets the criterion of "Inventive step".

The proposed solution meets the criterion of "industrial applicability", since the combination of characteristics characterizing it provides the possibility of its existence, performance and reproducibility, since well-known materials and equipment can be used to implement the proposed solution.

The method of firing PC MLRS is as follows.

To mislead the enemy as to the position of the MLRS launcher position 1, determined by the results of noting the KBB radar 13 parameters of the ballistic flight path of 15 rockets 2, the PC 2 flight path in the airspace with a variable profile specified by the UTP I, II and III is used. After deploying the MLRS launcher launcher 1 at the firing position, pointing it using the guidance device 4 in a horizontal plane in the direction of the target and lifting the guides from PC 3 to a small launch angle in the VP, the minimum value of which is limited by the technical characteristics of launcher 1 and the terrain in the launch area positions, and the maximum - by the conditions of non-detection of PC 2 at the initial section of the trajectory of the enemy radar KBB 13, is performed according to the signals received from the device for generating the command to turn on the engine and start PC 6, including the solid propellant rocket engine 9 and the launch of PC 2 at this small angle in the VP, after the estimated time t _I flight PC 2 on the initial portion of the flight path I, the value of which is determined in the calculator 5 PU 1 and enter using communication devices PU and PC 7 and 8 in SAKT 10 before starting PC 2, transfer PC 2 to a new flight path II with a large angle in the VP, mating with the PC flight section along the ballistic flight path III, simulating the launch of PC 2 from fictitious point F, remote from PU 1 on safety distance L _without excluding it defeat by enemy artillery fire according to the results of noticing the KBB radar 13 of the launch position of the MLRS (PU 1), as well as ensuring that the PC 2 flying along the ballistic trajectory section III is in the vicinity of the target 12 intended for hitting, and the PC 2 flight path is changed using gas-dynamic the rudders 11 according to commands from SAKT 10, which form, in accordance with the required law, the pitch angle changes PC 2, which provides the initial section of the trajectory I with the ballistic flight path III by moving PC 2 in those the time t _II along the path II section with a large angle in the VP, the curvature of which is determined by the set value of the PC 2 overload created in the VP. In this case, the values of the flight time PC for the initial USP t _I and USP with a larger angle in the airspace t _{II are} determined in the calculator 5 PU 1 according to the formulas obtained using the ratios and variables shown in FIG. 2:

,

,

,

,

,

,Where

,

,

In this way, effective firing at target 12 is ensured under counter-battery conditions while maintaining high stealth from the enemy’s KBB radar and, therefore, high survivability of the launcher in the conditions of enemy fire reaction.

Let us conduct a quantitative analysis of the effectiveness of the proposed method of firing a PC MLRS. In the general case, the probability of an object being hit by a missile (R _RS ) is calculated by the formula (Zotov V.P. Probabilistic Basics of Weapon Efficiency Assessment Methods, Issue 1. - M .: VA named after F.E.Dzerzhinsky, 1983, p. 111) :

where R _launcher , n - the probability of launcher launcher fire with artillery (MLRS) of the enemy and the number of starts (shots) at it, respectively;

P _nc , P _then - the conditional probabilities of MLRS preparation for shooting at the target (calculation and input of installations for shooting, target guidance, preparation of the PC for use, etc.) and the destruction of the object by the warhead of the PC, respectively.

Since the maximum detection ranges of firing MLRS with modern KBB radars, for example of the AN / TPQ-37 (V), EQ-36 type, are 60-70 km, and the positions of the MLRS launchers are removed from the front line (LF) at a distance of no more than 20-30 km, then in almost any situation the PC’s flight path will be tracked by the enemy’s KBB radar, and the location of the MLRS launcher will be determined with an accuracy of 30 m to (0.3-1)% of the range to the launcher (Krupnikov A. Counter-battery radar of foreign countries. 2010. No. 12).

Therefore, the situation was considered when the MLRS launcher was 20 km away from the LF, and the KBB radar station was 10-30 km away and scanned horizontally in a 90-degree sector. at an elevation angle of 1.65-2.45 degrees. respectively. The effectiveness of the proposed method of shooting was evaluated on a simulation model developed using the Mathcad 14 application software package. In this case, the spatial motion of the PC in all three sections (I, II, and III) of its flight path, as well as the movement of the PC along the prototype’s fire path (trajectory) were modeled in detail. fifteen). When modeling, the following hypothetical initial data were adopted characterizing the prototype and the proposed solution. It was believed that in the prototype and in the proposed method of firing, the probabilities of MLRS preparation for firing at the target P _{ps are the} same and equal to 0.95. The permissible PC overload in the airspace n _{y was} taken to be 4, and the flight speed V, equal to 600 m / s. As KBB radars, the AN / TPQ -36 (V) and -37 (V) radars of the FIREFINDFR radar complex were considered, and MLRS-type MLRS as artillery firearms.

The probability of hitting missiles with MLRS R missiles П _launchers and the number of PC launches on it n were determined on the simulation model, and it was believed that the strike was delivered 30 s after the radar was detected by the KBB radar of the launcher position.

The probability P _{then was} calculated by the formula (Fendrikov N.M., Yakovlev V.I. Methods of calculating the combat effectiveness of weapons. - M.: Military Publishing House, 1971, p. 59):

,

,

where R _p , E, ρ is the reduced radius of the target’s destruction of the high explosive warhead PC, the median shooting error and the normal distribution constant (ρ = 0.476), respectively.

It was believed that the deviation of the PC during shooting from the aiming point is 0.21% of the range, which when shooting at 70 km gives a median (probable) range error of a shot of 150 m (Korablin V. Russky SMERCH. Weapon Magazine, No. 9 (20) .- M .: Vostochny Horizon, 1999, p. 19), and the warhead of the PC has a mass of 250 kg, which, as shown by the calculations carried out according to the methodology (Pilot and Navigator Handbook. Edited by the Military Navigator of the USSR, Lieutenant General of Aviation MV Lavsky. - M .: Military Publishing House, 1974, p. 448), has a sufficiently large reduced radius destruction of typical targets (for a zone of weak destruction of structures with a high explosive action) equal to 400 m.

As a result of the simulation, it was found that when the radar is 10 km away from the LF and the airborne field of view is 2.45 degrees, the height H _without at which the PC does not detect KBB radar is 951 m at the boundary located 6 km from the PU position towards the LF (point F). To shoot at a target 46 km away from the launcher, in these conditions the following settings for launching the PC should be adopted: α _pF = 40 deg, α _pm = 7.6 deg, Δ = 2 deg, Δα = 33.4 deg. The flight time of the PC in accordance with USP I shall be 0.8 s, and according to USP II - 11.3 s. In this case, starting from a height of H _without , the PC will move along a ballistic trajectory, the extrapolation of which by the enemy based on the results of serrations of the KBB radar will lead to an erroneous determination of the location of the launcher (at point F, 6 km away from the launcher towards the LF, instead of the true position).

When using the traditional method of firing PC MLRS (prototype) in counter-battery conditions, the probability of hitting a target does not exceed a value of 0.2, and when shooting the proposed method provides a significantly higher probability of hitting a target with one PC (at least 0.8).

An analysis of the results shows that the proposed method of firing a PC MLRS provides an increase in the probability of hitting a target of a PC in counter-battery combat four times (from 0.2 to 0.8) compared to the prototype and can be considered as the main method of firing a PC with active fire counteraction of the enemy.

The above information indicates the possibility of the implementation of the claimed method of shooting PC MLRS the following set of conditions:

the proposed method of firing a PC MLRS when it is implemented will increase the efficiency of firing a PC MLRS by 4 times due to the high survivability of the MLRS launcher in counter-battery combat by using a trajectory that simulates starting the PC from a fictitious point remote from the launcher at a safe distance, eliminating fire damage enemy artillery according to the results of notching the launch position of the MLRS radar stations KBB;

the possibility of putting into practice the claimed method of firing a PC MLRS as shown in the claims using the means and methods described in the application or known prior to the priority date is shown;

the proposed method of firing a PC MLRS, during its development, is able to ensure the achievement of the technical result perceived by the applicant.

Claims (1)

A method of firing rockets (PC) of multiple launch rocket system (MLRS) in counter-battery conditions, which consists in pointing the launcher (launcher) in a horizontal plane in the direction of the target, lifting the guides from the PC to a predetermined launch angle in the vertical plane (VP), turning on the solid propellant rocket engine and starting up the PC followed by flight along a predetermined ballistic trajectory, the deviation from which is eliminated by controlling the pitch and yaw angles of the PC using gas-dynamic rudders according to commands from autonomous flight path correction (SAKT) PC systems, characterized in that before starting the PC along a predetermined ballistic path, the PC is first launched at a small angle in the VP along the initial portion of the flight path (UTP) PC, after the estimated PC flight time over the initial portion the trajectory, the value of which is entered into SAKT before starting the PC, transfer the PC to a new trajectory with a large angle in the VI, and the minimum value of the initial angle of start of the PC in the VI is limited by the technical characteristics of the PU and the relief fom of the terrain in the area of deployment of the launcher, and the maximum - by the conditions of non-detection of PC at the initial portion of the trajectory of the enemy's radar station (radar) counter-battery combat (KBB), after which the flight of the PC is carried out along a predetermined ballistic trajectory that simulates the launch of the PC from fictitious point F, remote from the launcher the safe distance L _without precluding its defeat the enemy artillery fire on the results of radar serifs HEC starting position MLRS, the conjugation of all sections of the trajectory PC flight carried out so that the PC, moving l along a predetermined ballistic trajectory, hit the target designated for destruction, and changing the PC flight path using gas-dynamic rudders according to commands from SAKT, which form, in accordance with the required law, changes in the pitch angle of the PC, which ensures the conjunction of the initial UTP with the flight path with a large angle in VP and USP along a ballistic trajectory, while the values of the flight time PC along the initial USP t _I and USP with a large angle in VP t _{II are} determined by the formulas:

Where

N _without - safe flight altitude of the PC, excluding its detection of radar KBB; D _RS , D _radar - removal of PU and radar from the front line (LF), respectively;
β is the minimum viewing angle of the radar KBB in the vertical plane (VP);
α _pF is the fictitious launch angle of the PC from point F, at which the flight of the PC along the USP III is ensured;
α _pm is the start angle of the PC in the airspace at which the PC, moving in a straight line, crosses the bottom of the KBB radar at a height of H _without ;
θ is the angle of the velocity vector PC;
Δ is the correction to the start angle of the PC, necessary for pairing the II UTP with I and III UTP PC taking into account permissible PC overloads in the VP;
V, n _y - PC flight speed and allowable PC overload in the airspace, respectively;
g is the acceleration of gravity.

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