RU2241202C2 - Method for location of rocket in flight trajectory - Google Patents

Abstract

FIELD: armament test.

SUBSTANCE: at the moment of bursting of the rocket warhead the mutual position of the injurious component of the rocket warhead in the section of the spatial field of their dispersion after blasting is registered and determined with the aid of an indicator of the position of injurious components, and then, according to the characteristics of the field of injury of the position indicator, the position of the injurious components of the warhead at the moment of bursting is determined on the thin-walled easily pierceable screen stationary installed in the spatial area of their dispersion between the underlying surface and the rocket, and connected to the underlying surface.

EFFECT: enhanced accuracy of rocket location relative to the underlying surface at the moment of bursting in any meteorological condition, simplified procedure of test, and reduced time of obtaining of information.

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Description

The present invention relates to the field of weapons testing and can be used in the development of warheads of missiles and shells.

A known method [1] of detecting the location of a moving object, involving the presence of a transceiver having several antennas mounted on a moving object, and one or more radio links. The location of the object can be determined at a ground station by the combination of code signals at the time they arrive at the receiver or communication line.

The disadvantage of this method is that for its implementation it is necessary to install a special device at the facility that is not conducive to the fulfillment of the combat mission, which leads to an increase in mass, dimensions and complexity of the design of ammunition.

A known method [2] of determining the location of a rocket (ammunition) on the flight path without placing any special devices on it. This is a method of external trajectory optical measurements based on visual tracking of an object, and a device for implementing this method containing a missile (ammunition) and a training ground with means of external trajectory measurements. However, the disadvantage of this method and its corresponding device is that the accuracy of determining the location of the rocket depends on the state of the atmosphere at the time of observation of the object, the individual characteristics of the operators and the distance to the flying object. Also, the accuracy of positioning is affected by errors caused by inaccurate installation of film theodolites, the non-simultaneous operation of their shutters, alignment of optical equipment, and the error of the tracking system, i.e. all inaccuracies in the operation of measuring equipment.

When testing missiles (ammunition), the accuracy of determining their location at the time of detonation is especially important, since on the determined location they judge the accuracy of the missile guidance systems on the target and the effectiveness of its combat equipment.

The objective of the invention is to eliminate the above disadvantages, namely: improving the accuracy of determining the location of the rocket relative to the underlying surface at the time of its detonation in the absence of external trajectory measurements at the test site, in any meteorological conditions, as well as simplifying testing and reducing the time for obtaining information.

This problem is achieved by the fact that in the method of determining the location of the rocket on the flight path, based on the registration of the signal from the rocket, register and determine the relative position of the striking elements of the warhead of the rocket in the cross section of the spatial region of their expansion after undermining using an indicator of the position of the striking elements, and then the characteristics of the lesion field of the position indicator determine the position of the damaging elements at the time of detonation.

This method is implemented due to the fact that an indicator of the position of the striking elements of the warhead of the missile after its detonation in the form of a thin-walled easily penetrated screen installed stationary in the spatial region of their expansion is introduced into the device containing the missile warhead with a spatial region of expansion of the striking elements and the underlying surface. between the underlying surface and the rocket and connected to the underlying surface.

The essence of the invention lies in the fact that the determination of the relative position of the scattered striking elements after undermining the rod warhead of the rocket allows, knowing the characteristics of the battlefield of the warhead, to determine their initial position at the time of detonation, and through it the location of the rocket at the time of detonation with an accuracy that depends only from tolerances on the characteristics of the lesion field and errors in determining the relative position of the striking elements.

Moreover, the latter can be performed accurately (determined by the accuracy of the measuring tool), because the position of the striking elements is fixed on the traces of the penetration of the position indicator, made in the form of a thin-walled easy-to-break screen installed stationary in the spatial area of their expansion between the underlying surface and the rocket.

Figure 1, 2, 3 presents diagrams explaining the proposed method and the corresponding device for its implementation, where:

1 - missile with warhead (warhead);

2 - spatial region of expansion of the striking elements, limited by conical surfaces;

3 - indicator of the position of the striking elements of the warhead in the form of a screen;

4 - zone of breaking through traces from the damaging elements of warheads (lesion field);

5 - underlying surface;

6 - the central director-shooting line;

7 - control cards (figure 2, 3);

8 - a plane passing through the axis of symmetry of the zone of penetration of traces from the striking elements, and perpendicular to the screen indicator position;

l is the length of the zone of penetration of traces on the screen of the indicator of the position of the striking elements;

x is the coordinate of warhead detonation in the horizontal plane;

y is the coordinate of warhead detonation in the vertical plane.

A device for implementing the method is a missile with a warhead 1 with a spatial region of expansion of the striking elements bounded by conical surfaces 2, and an indicator of the position of the striking elements 3 in the form of a thin-walled easily penetrated screen, for example: sheets of plywood or plastic film attached to the underlying surface 5 - the ground . The rocket is launched according to the central director 6, which determines the line of fire. After undermining the warhead of rocket 1, the striking elements scatter in the spatial area bounded by the conical surfaces 2. On the thin-walled screen of the position indicator 3 of the striking elements, a zone 4 of breaking through traces of the striking elements is formed, in the form of a parabola, limited by sections of the conical surfaces 2 and the screen of the position indicator 3. When this, the longitudinal axis of the rocket 1 lies in a plane passing through the axis of symmetry of zone 4 of breaking through traces of striking elements, perpendicular to the screen of the position indicator 3.

The coordinates of the rocket relative to zone 4 are determined by control cards 7, which is an image of zone 4 on a scale. Cards are prepared in advance before firing and theoretically calculated for various speeds, X, Y coordinates of the rocket, and warhead characteristics, at the time of warhead detonation. The more control cards, i.e. the calculations are done with a smaller step, the higher the accuracy of determining the coordinates of the undermining of the warhead missiles. If the size of the penetration trace on the indicator screen does not coincide with the size of the traces on the card, then take two control cards with the size of the traces, one of which is smaller than the trace on the indicator screen, and the other is larger than the trace on the indicator screen, and the coordinates of the warhead detonation to increase accuracy are determined by the method interpolation.

The proposed method and device allows for more accurate measurements of the location of the rocket at the time of its detonation compared to the known ones and can find application in developing combat equipment and guidance systems. It is particularly preferable to use the proposed method and device when measuring miss when firing at a fixed target simulator under any meteorological conditions without the use of external trajectory measurements.

Sources of information

1. Japanese application No. 56-23106 of July 16, 74 - an analogue.

2. Book A.A. Dmitrievsky "The movement of rockets", M., Military Publishing House, 1968, p. 440, p. 449 - prototype.

Claims (1)

A method for determining the location of a rocket on the flight path at the time of undermining its warhead, which consists in registering and determining the relative position of the striking elements of the warhead of the rocket in the cross section of the spatial region of their expansion after blasting using the position indicator of the striking elements in the form of a thin-walled easily penetrated screen installed stationary in the spatial region of the expansion of the striking elements, then by interpolation using the obtained characteristics of the indie lesion field Ator position, as well as ready-made control cards representing image fields lesion calculated theoretically for different speeds, and the missile coordinate characteristics at the time of warhead detonation determine location coordinates for missile flight path at the time of its warhead detonation.

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