RU2240493C1 - Time fuze of shells of salvo-fire jet-propelled systems (sfjps) - Google Patents

Abstract

FIELD: use of shells of salvo-fire jet-propelled systems, when the fixed rate of fire needs automatic programming in the interval between launchings of shells adjacent in time.

SUBSTANCE: the time fuze has a power supply source, electronic timing device, safety-actuating mechanism and a receiving device, the induction coil is positioned on the outer surface of a tubular ferrite core. Installed in the inner cavity of the core is a screen of soft magnetic metal placed in which screen of soft magnetic metal placed in which is a capacitor supply source, electronic timing device with an inertia switch, additionally used is a selector of programming command pulses. The induction coil has taps from the inner turns, which via a rectifier are connected to the input of the pulse selector and via an additional diode - to the capacitor supply source, and the output of the pulse selector is connected to the adjusting input of the electronic timing device, connected to whose power line is the capacitor supply source. The programming command pulse selector has a differentiating circuit of a capacitor and a resistor with a time constant equal to the duration of the adjusting programming command pulse, and a diode. The efficiency of target destruction is enhanced due to enhanced accuracy of remote action time countdown and enhanced efficiency of conversion of electromagnetic field to an electric signal at programming, i.e. at transmission of energy for electric power supply of the fuze electronic circuit and programming signals in the conditions of a fixed rate of fire of the SFJPS.

EFFECT: enhanced efficiency of target destruction.

2 cl, 4 dwg

Description

The invention relates to military equipment, mainly to fuses of rockets of multiple launch rocket systems (MLRS). A feature of the area of use of shells is the normalized rate of fire, and this circumstance requires the fuse to be programmed in automatic mode in a pause between the launches of adjacent shells.

Known fuses, programmable remotely, by patents: US No. 6557450, IPC F 42 C 17/00, published May 6, 2003, US No. 6484115, IPC F 42 C 11/04, published November 19, 2002, US No. 6138547 , IPC F 42 C 17/00, published on 10/31/2000, US No. 5817958, IPC F 42 C 11/06, published on 10/27/1998, US No. 5117732, IPC F 42 C 17/04, published 02.06. 1992, US No. 4664013, IPC F 42 C 11/06, published 05/12/1987, US No. 4144815, IPC F 42 C 11/04, published 3/20/1979, US No. 3371579, IPC F 42 C published on 03/05/1968

Known remote fuse according to US patent No. 4022102, IPC F 42 C 17/00, published 05/10/1977, the programming of which is carried out by an electromagnetic field created by two coils mounted coaxially with the gun barrel, outside the front cut of the barrel. The fuse receiver is located in the bottom of the projectile. The use of such a device for MLRS shells is impossible due to the need to lay the cable inside the engine compartment of the rocket, the short time the projectile passes through the transmitting device, which makes it difficult to efficiently transfer energy and fuse programming signals.

The device according to US patent No. 6170377, IPC F 42 C 17/00, published on January 9, 2001, proposes a remote fuse programmed with an electromagnetic field through a pickup coil located on the shell of the projectile. However, due to the influence of the metal casing, in which eddy currents absorbing field energy arise when programming with an electromagnetic field, the signal transmission efficiency in multiple launch rocket launcher mode is insufficient.

Closest to the claimed technical solution is a remote fuse of an artillery shell according to US patent No. 4750424, IPC F 42 C 9/00, published on 06/14/1988. In this device, fuse programming can occur automatically during loading and manually. The fuse contains a power supply battery, an electronic temporary device (microcomputer), an adjusting ring for manual installation, a display for displaying entered information, an ignition circuit, an initial blocking device (long cocking), a receiving coil of an inductive communication line with a resonating capacitor. When combining the installer’s transmitting coil with the fuse case according to US patent No. 4750424, F 42 C 9/00, selected as a prototype, an alternating current flows through the installer’s coil and an alternating electromagnetic field arises, which, piercing the fuse’s receiving coil, excites an alternating current voltage. After rectification, a constant voltage, supplied to the key circuit, connects the battery to the electronic temporary device. Programming signals containing information about the time of remote action are stored by an electronic temporary device. At the same time, information on the entered time appears on the fuse display. When fired, the temporary device lock is released and the countdown of the remote action begins. After the set time has elapsed, the electronic device (microcomputer) generates an ignition signal, which activates the warhead. With the manual version of the fuse programming, the mounting ring is rotated and the electrical contacts are closed, with the help of which power is supplied to the electronic temporary device and a series of pulses are generated that program the microcomputer.

Common signs of the claimed invention with the prototype is the presence in the fuse of a power source, an electronic temporary device, a safety-executive mechanism and a receiving device, which includes a receiving coil and a resonating capacitor.

Contactless transmission and reception of programming signals are possible with minimal gaps between the receiving coil of the fuse and the transmitting coil of the installer, that is, when they are placed in the same plane. Fulfillment of this condition for multiple launch rocket systems presents significant difficulties, since complex and high-speed mechanisms are necessary for combining and uncoupling the coils during the firing process. Another disadvantage of the prototype is the placement of the receiving coil on the electrically conductive housing of the battery. Being a short-circuited coil inductively coupled to the receiving coil, the battery case reduces the quality factor of the receiving circuit, which leads to a decrease in efficiency inductive communication and control lines.

The objective of the invention is to increase the effectiveness of hitting a target during multiple launch rocket launchers MLRS by increasing the accuracy of counting the time of remote action and increase efficiency the conversion of the electromagnetic field into an electric signal during programming, that is, when transferring energy to power the electronic circuit of the fuse and programming signals in the normalized rate of multiple launch rocket launcher MLRS.

The technical result of increasing efficiency is achieved by introducing into the design of the fuse a capacitor power source, a pulse selector, a receiving induction coil with taps, a ferrite tubular core. A half-wave rectifier is connected to the taps of the coil.

The essence of the claimed invention lies in the fact that the remote fuse containing a power source, a rectifier, a diode, an electronic temporary device connected by an output to a safety-actuating mechanism, and a receiving device including an induction receiving coil and a capacitor forming a receiving circuit are equipped with a tubular ferrite core , a screen made of soft magnetic material, an inertial contactor, a pulse selector of a programming command, and the induction receiving coil has taps of internal coils, whereby a capacitor power source is used as a power source, while the induction receiving coil is placed on the outer surface of the tubular ferrite core, in the inner cavity of which there is a capacitor power source enclosed in a screen made of magnetically soft material, an electronic temporary device and a pulse selector for programming commands, one of the taps from the internal turns and one of the extreme turns of the induction receiving coil through a rectifier are connected about the input of the pulse selector of the programming command and through the diode to the capacitor power supply and the inertial closure, the output of the pulse selector of the programming command is connected to the installation input of the electronic temporary device, the capacitor power source is connected to the power bus, and the inertial contactor is connected to the “Start” bus, the second the tap from the internal turns is connected to a common bus. The pulse selector of the programming command contains a differentiating circuit of a capacitor and a resistor with a time constant equal to the duration of the installation pulse of the programming command, and a diode. A tubular ferrite core is introduced to eliminate the losses introduced by the screen into the receiving circuit, to increase the sensitivity of the induction receiving coil and to increase the efficiency The core wall thickness should exceed the depth of penetration of electromagnetic waves (skin layer) into the core by at least 2 times, at the working frequency of the inductive fuse control line, due to which the electromagnetic field is practically absent in the inner cavity of the tubular ferrite core. The conversion of the installer's electromagnetic field (not shown in the drawings) into the charge energy of a capacitor power source and into the energy of electrical programming signals is carried out with high efficiency

The device of the proposed technical solution is illustrated by drawings:

Figure 1 presents a structural diagram of a fuse.

Figure 2 shows the structural diagram of the fuse.

Figure 3 presents the electrical circuit of the proposed technical solution.

Figure 4 shows the sequence diagram of the fuse.

The fuse (Fig. 1) consists of a dielectric housing 1, a target reaction sensor 2, a safety-actuating mechanism 3, an electronic temporary device 4 with an inertial closure 5, a rectifier 6, a pulse selector for the programming command 7, an induction receiving coil 8 with taps, a capacitor source power 9, a ferrite core of a tubular shape 10, a screen of soft magnetic material 11.

The fuse block diagram shown in FIG. 2 includes an induction receiving coil 8, a rectifier 6, a capacitor power supply 9, a pulse selector for a programming command 7, an inertial contactor 5, an electronic temporary device 4 and a safety-actuating mechanism 3.

Figure 3 shows a diagram of the electrical connections of the elements of the fuse. The receiving circuit consists of an induction receiving coil 8 (L1) with a core 10 and taps a, b, c, d, and taps a and d are from the extreme turns, b and c are from the internal turns of the induction receiving coil 8, capacitor C1, a resistor R1. Rectifier 6 consists of two diodes VD1 and VD2. Coil 8 is connected by its tap b to the anode of the diode VD1 of rectifier 6, tap d is connected to the anode of the diode VD2 of rectifier 6, tap "c" is connected to the common bus 04 of the electronic temporary device 4. The cathodes of the diodes VD1 and VD2 are combined and connected through the diode VD3 to the capacitor a power source 9, an inertial closure 5, and a power bus 03 of the electronic temporary device 4. The cathodes of the diodes VD1 and VD2 of the rectifier 6 are connected to the input of the pulse selector of the programming command 7, consisting of a capacitor C2, a resistor R2, and a diode VD4. The output of the pulse selector of the programming command 7 is connected to the input 01 “Installation” of the electronic temporary device 4. The second output of the inertial contactor 5 (SA) is connected to the input 02 “Start” of the electronic temporary device 4. Terminal 05 - “Output” - the electronic temporary device 4, connected to the safety-actuating mechanism 3 at the input 06.

Figure 4 presents the sequence diagram of the fuse. On figa shows the control signals of fuses of shells participating in the volley. Under the influence of the electromagnetic field of the installer (not shown in the drawing), rectangular pulses 12, 13, 14, 15, 16, modulated by alternating voltage (U) appear on the induction receiving coil and, accordingly, on the receiving circuit L1C1R1. Pulse 12 transfers energy to the charge of the capacitor power source (E), the pulses 13, 14 are programming, that is, with their help information about the time of remote action is transmitted to the first volley shell. The groups of pulses 15, 16 are the control for i, i + 1 shells participating in the salvo. Figure 4b shows the voltage waveform E of the signals shown in Figure 4a after the rectifier 6. Signals 17, 18, 19 and onwards are similar signals for i, i + 1 shells. On figv presents a graph of 20 changes in voltage across the capacitor power supply Ekip on the flight path of the projectile. Graph 21 (FIG. 4d) shows the change in inertial overloads (n) in the active section of the trajectory. On fig.4g marked: t1 - the moment of starting the rocket engine, t2-moment of achievement of inertial acceleration of the value corresponding to the response threshold 22 of the inertial contactor 5. At time t3, corresponding to the end of the countdown of the remote action, the signal 23 is generated , which enters the safety-actuating mechanism 3.

The fuse is as follows. The apparatus for preparing and launching shells (not shown in the drawings) generates programming signals and transfers them to the fuse in the form of electromagnetic field pulses. On the induction receiving coil 8 and the receiving circuit of the fuse there are programming signals 12, 13, 14 in the form of alternating voltage pulses.

With rectifier 6, pulses 12, 13, 14 are converted into pulses 17, 18, 19. Pulse 17 charges the capacitor power supply 9, and pulses 18 and 19 are supplied to the pulse selector of programming command 7 and then to programming input 01 - “Installation” - electronic temporary device 4, where the time interval between pulses 18 and 19 is proportional to the time of the remote action of the fuse. This ends the fuse programming. Then, a command to turn on the engine is received from the apparatus for preparing and launching the projectile, at time t1 the projectile begins to move and inertial overloads (acceleration) 21 occur, which at time t2 reach the value n = n1 corresponding to the response threshold 22 of the inertial contactor 5. From time t2 the countdown of the remote action of the fuse begins, which ends with the formation of the command 23 arriving at the safety-actuating mechanism 3, separating the warhead from the engine and opening the brake th parachute. When meeting with the surface of the earth, the reaction sensor of target 2 is triggered and the warhead is activated.

A remote fuse of rockets of multiple launch rocket systems, made in accordance with the invention, allows to increase the efficiency of hitting a target during multiple launch rocket launchers MLRS by improving the accuracy of counting the time of remote action and increase efficiency the conversion of the electromagnetic field into an electric signal during programming, that is, when transferring energy to power the electronic circuit of the fuse and programming signals in the normalized rate of multiple launch rocket launcher MLRS. In addition, the remote fuse can improve the reliability of the entire MLRS system by eliminating the impact on the electronic circuit of the fuse of external electromagnetic fields of radar stations, connected radio stations and other sources of interference.

Improving the efficiency of multiple launch rocket launch rocket systems using the claimed invention is confirmed by the results of laboratory and field tests.

Claims (2)

1. A remote fuse of rockets of multiple launch rocket systems containing a power source, a rectifier, a diode, an electronic temporary device connected by an output to a safety-actuating mechanism, and a receiving device including an induction receiving coil and a capacitor forming a receiving circuit, characterized in that it equipped with a tubular ferrite core, a screen made of soft magnetic material, an inertial contactor, a pulse selector of a programming command, and an induction receiving coil named after there are taps from the internal turns, and a capacitor power source is used as the power source, while the induction receiving coil is placed on the outer surface of the tubular ferrite core, in the inner cavity of which there is a capacitor power source enclosed in a screen made of magnetically soft material, an electronic temporary device and a pulse selector programming commands, one of the taps from the internal turns and one of the extreme turns of the induction receiving coil through the rectifier connected to the input of the pulse selector of the programming command and through the diode to the capacitor power supply and the inertial closure, the output of the pulse selector of the programming command is connected to the installation input of the electronic temporary device, the capacitor power supply is connected to the power bus, and the inertial contactor is connected to the “Start” bus, the second tap from the inner turns is connected to a common bus. 2. The remote fuse according to claim 1, characterized in that the pulse selector of the programming command comprises a differentiating circuit of a capacitor and a resistor with a time constant equal to the duration of the installation pulse of the programming command, and a diode.

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