RU2240494C1 - Device for transmision of information for contactless programming of time fuzes of shells of salvo-fire jet-propelled systems - Google Patents

Abstract

FIELD: military equipment.

SUBSTANCE: the device has a radiating inductance coil with two windings and a ferrite core interrelated with the gun barrel (of the guiding fighting vehicle), resonating capacitor and an outer screening body installed in which is the radiating inductance coil with series-connected windings, annular and rod-type ferrite cores. One winding is positioned on the outer surface, and the second one with the rod-type core-inside the annular core. The rod-type core is made for movement inside the annular core, which provides adjustment of the radiating inductance coil to resonance with the carrier frequency of the input programming signals. The cores of the radiating coil are fastened with an interaxis distance equal to (0.55-0.8) of the caliber in parallel with the base of the screening body, and accordingly with the barrel axis (guiding) on its outer surface above the available through rectangular slot.

EFFECT: provided transmission of information for contactless programming of time fuzes of preloaded shells directly in the automatic mode of fire from multibarreled fighting vehicles of salvo-fire jet-propelled systems.

2 cl, 3 dwg

Description

The invention relates to the field of military equipment, and more particularly to information transmission devices for contactless programming of remote fuses of shells in the automatic mode of firing from charged combat vehicles of multiple launch rocket systems.

Known devices for transmitting information for contactless programming of fuses (US patents No. 469796, IPC F 42 C 17/00, publ. 03/17/86, US No. 4862785, IPC F 42 C 17/00, publ. 09/09/89; US No. 5343795, IPC F 42 C 17/04, published September 6, 1994; US No. 6176168, IPC F 42 C 11/04, published January 23, 2001; International Application No. WO 01/57468 A1 of August 9, 2001; European Patent No. EP 1166036 , IPC F 42 C 17/04, published 01.02.2002; FR No. 2829834, IPC F 42 C 17/04, published 21.03.2003). These devices are made on the basis of radiating inductance coils and provide information transfer for contactless programming of a fuse of a single artillery shell before loading the gun, and therefore cannot be used to obtain the required technical result.

A device for transmitting information for contactless programming of an artillery projectile fuse is known (US patent No. 5117733, IPC F 42 C 17/04, publ. 02.06.92). The device contains a radiating inductor with a core made up of individual ferrite elements, and two unconnected windings (main and auxiliary) of stitched flat wire layers. The coil is in the form of a segment of a tube. In the breech housing there is a dovetail-shaped groove in which a coil is mounted and poured. An electric current constantly passes through the main winding. When the voltage in the auxiliary winding changes as a result of the projectile feeding into the breech section, signals are generated in the main winding that are transmitted to the receiver of the programmable fuse. The specified device is taken as a prototype.

Common features of the invention and the device adopted for the prototype is the presence of a radiating inductance coil with two windings and a ferrite core interconnected with the barrel of the gun (guiding combat vehicle).

The reasons that prevent obtaining the required technical result are that the device provides information for contactless programming of the fuse only for a single projectile when it is fed into the breech of the gun (when loading), which leads to a long programming time of the fuse and, as a result, decrease in rate of fire; requires a mechanism for feeding (loading) the shell into the breech; excludes the possibility of transmitting information for contactless programming of a fuse of a charged projectile.

The problem to which the invention is directed, is to provide information for non-contact programming of remote fuses of pre-charged shells directly in the automatic mode of firing from multiple-barrel combat vehicles of multiple launch rocket systems.

The essence of the invention lies in the fact that a capacitor, a second ferrite core and an external ferrite core are introduced into the information transfer device for non-contact programming of remote fuses of rockets of multiple launch rocket systems, which contains a radiating inductance coil with two windings and a ferrite core interconnected with the gun’s barrel or guiding combat vehicle a shielding case, and the windings are connected in series, the radiating inductor and the capacitor are connected between in series or in parallel, one of the ferrite cores is made ring-shaped, and the second is rod-shaped, while the radiating inductor, the ring-shaped and rod-shaped ferrite cores are installed inside the shielding case, one winding is placed on the outer surface of the ring-shaped core of length L with external Disl. and internal Dvn. diameters, and the second winding and the core core length Lct. and a diameter d are placed inside the ring-shaped core, and the core core is arranged to move inside the ring-shaped core so that the resonant frequency of the alternating electromagnetic field of the radiating inductor corresponds to the carrier frequency of the programming input signals, with D.sl. = (3.5-4.5) d, Dint. = (1.5-2.5) d, L = (2.5-3.5) Lst. and the wall thickness of the annular core (Dl. - Dint.) >> δ, where δ is the penetration depth of the electromagnetic field into the core material, the distance between the parallel axes of the barrel (guide) and the cores of the radiating inductor B = (0.55-0.8 ) Dк, where Dк is the caliber of the projectile, the ring-shaped and rod cores of the radiating inductor are fixed in the external shielding case parallel to its base, and the case is mounted on the outer surface of the gun barrel or guide of the combat vehicle having a through rectangular groove width H = (1.5-2.5) D and length C = (2.5-3.5) N.

The coaxiality of the cores of the radiating inductor and the possibility of their movement relative to each other is achieved by introducing a sleeve with an external thread and a smooth sleeve mounted on the ends of the core core, a frame with an internal thread and a groove under the winding installed inside the ring-shaped core, two clamps for the position of the coil, two of its racks fastenings in an external shielding case and wedge-shaped parts.

Information transfer devices for a projectile of caliber Dк = 120 mm, have optimal characteristics with the following design parameters. Ring-shaped core: Dl. = 30 mm, Dv. = 16 mm, L = 84 mm, (Dl. - Dv.) = 14 mm, which is much more than δ = 0.5 mm, the depth of penetration of the electromagnetic field into the core material for a given carrier frequency Fnes. Core core: d = 8 mm and Lst. = 30 mm. The distance between the parallel axes of the cores of the radiating inductor and the trunks (guides) B = 70 mm. Width H = 50 mm and length C = 150 mm of a through rectangular groove on the barrel (guide). The invention is illustrated by the following drawings:

- design of a device for transmitting information - figure 1;

- functional diagram of a device for transmitting information - figure 2;

- structural diagram of the placement of the information transfer device on the trunk (guide combat vehicle) - figure 3.

The design of the information transmission device shown in figure 1, includes:

- external shielding housing 1;

- detail wedge-shaped form 2;

- a radiating inductor 3 in a dielectric casing containing an annular ferrite core 5 with an external D and internal Dvn. diameters of length L, two windings 4 and 8 connected in series, a rod ferrite core 6 of diameter d with length Lst., at the ends of which a sleeve 15 with an external thread and a smooth sleeve 7 are installed;

- frame 9 with internal thread and a groove under the winding 8;

- two position locks 10 and 16;

- capacitor 13;

- a connector (connector) 12 for connecting to a source of programming signals;

- racks of dielectric material 11 and 14 for mounting the radiating inductor 3 in the external shielding housing 1.

Functional diagram of the information transmission device shown in figure 2, includes:

- external shielding housing 1;

- capacitor 13;

- a radiating inductor 3 with two series-connected windings 4 and 8;

- programmable fuse 17 with a receiving device 18;

- shell 19 in the barrel (guide) 20;

- shaper programming signals 21 combat vehicle.

The structural layout of the device for transmitting information on the barrel of the gun or guide combat vehicle, shown in figure 3, includes:

- an external shielding housing 1, mounted above an open rectangular groove of a width H and a length C available on the gun or the guide of the combat vehicle 20;

- a radiating inductor 3, which is a wedge-shaped part 2 fixed parallel to the base of the housing 1 so that the cores 5 and 6 are fixed on the outer surface of the gun’s barrel or guiding combat vehicle 20 with a center distance B;

- programmable fuse 17 with the receiving device 18 of the projectile 19 in the barrel of the gun or in the guide combat vehicle 20 caliber Dk.

The design of the device (Fig. 1) for transmitting information comprises an external shielding housing 1 without a lower wall and with an internal inclined surface on the upper wall and a radiating inductor 3 in the dielectric housing. On the opposite walls of the housing 1 there are two fastening posts 11 and 14, two position locks 10 and 16 with protrusions, the inner diameter of which corresponds to the outer diameter Dsl. ring-shaped core 5. The radiating inductor 3 contains a ring-shaped 5 and rod 6 ferrite cores and two series-connected windings 4 and 8. The winding 4 is placed on the outer surface of the core 5 of length L with an external Dzl. and internal Dvn. diameters. A core 6 with a diameter d and a length Lt., On the ends of which a sleeve 15 with an external thread and a smooth sleeve 7 are fixed, is installed in a frame 9 with an internal thread, in the groove of which a winding is wound 8. The frame 9 with a core 6 and a winding 8 is placed inside an annular core 5 with the possibility of axial movement of the core 6 inside the core 5, which ensures the tuning of the radiating inductor 3 in resonance with the carrier frequency of the programming signals Fnes. At the ends of the core 5, latches 10 and 16 are installed, which are mounted on the posts 11 and 14, and, respectively, on the opposite walls of the housing 1. The radiating inductor 3 by the wedge-shaped part 2 is fixed in the housing 1 so that the axis of the cores 5 and 6 are parallel to it base. The housing 1 is mounted on the outer surface of each barrel of the gun or the guiding combat vehicle 20 (Fig. 3), having a through rectangular groove of width H and length C with the center distance of the cores 5 and 6 and the barrel of the gun or guiding combat vehicle B.

The radiating inductor 3 and the capacitor 13 are connected in series or in parallel and are connected to inputs 21 of the programming signals with a carrier frequency Fnes via inputs 22 and 23. (figure 2).

 A device for transmitting information for contactless programming fuses of rockets of multiple launch rocket systems works as follows. When received on the inputs 22 and 23 of the programming signals with a carrier frequency Fnes. (Fig.2) a radiating inductor 3 creates an alternating electromagnetic field. The resonant frequency of the field corresponding to the carrier frequency of the signals is fixed when adjusted by the position of the core 6 inside the core 5 (figure 1). An alternating electromagnetic field is inductively transmitted through a rectangular through-groove of width H and length C in the guide 20 (Fig. 3) and on the receiving device 18 of the fuse 17 of the projectile 19 a variable EMF is induced, which is converted by the fuse into programming signals.

Thanks to the information transfer devices installed on each barrel of the gun or directing the combat vehicle, non-contact programming of fuses of pre-charged shells directly in the automatic mode of firing of multiple launch vehicles of multiple launch rocket systems is provided. At the same time, the reliability of information transfer is significantly increased and, as a result, the operational and tactical and technical characteristics of multiple launch rocket systems increase, which is confirmed by numerous field tests.

Claims (2)

1. Information transfer device for non-contact programming of remote fuses of rockets of multiple launch rocket systems containing an emitting inductance coil with two windings and a ferrite core interconnected with the gun’s barrel or the guide of the combat vehicle, characterized in that it is equipped with a capacitor, a second ferrite core and an external shielding body moreover, the windings are connected in series, the radiating inductor and the capacitor are connected together in series and whether in parallel, one of the ferrite cores is made ring-shaped, and the second is rod-shaped, while the radiating inductor, the ring-shaped and rod-shaped ferrite cores are installed inside the shielding case, one winding is placed on the outer surface of the ring-shaped core of length L with the outer D _ex. and internal D _vn diameters, and the second winding and the core core of length L _ct. and a diameter d are placed inside the ring-shaped core, and the core core is arranged to move inside the ring-shaped core so that the resonant frequency of the alternating electromagnetic field of the radiating inductor corresponds to the carrier frequency of the programming input signals, while D _ex. = (3,5 ÷ 4,5) d, D _int = (l, 5 ÷ 2.5) d, L = (2.5 ÷ 3.5) L _st. , and the wall thickness of the annular core (D _ex. - D _int ) >> δ, where δ is the penetration depth of the electromagnetic field into the core material, the distance between the parallel axes of the gun barrel or the guiding combat vehicle and the cores of the radiating inductor B = (0.55 ÷ 0.8) D _K. , where D _to. - caliber projectile, the ring-shaped and rod cores of the radiating inductor are fixed in an external shielding housing parallel to its base. 2. The device according to claim 1, characterized in that the outer shielding body is mounted on the outer surface of the barrel of the gun or guide combat vehicle, having a through rectangular groove of width H = (1.5 ÷ 2.5) D _ex. and length C = (2.5 ÷ 3.5) N.

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