RU2363924C1 - Method of blasting randem-type warhead and missile complex - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: invention relates to armaments and can be used in development of missile complexes, for examples, those that incorporate surface-base carriers. In compliance with proposed method, electric power fed from the surface power supply via tear-away communication wire is used to switch on locking circuit inhibiting the main warhead operation. Then, with the said communication wire torn away and missile at a required distance from the launcher, the independent locking signal is generated by the missile circuitry. Proposed missile complex differs from known designs in that its missile additionally comprises contact pickup, integrating circuit, while the electronic delay circuit includes input device and 1^st locking device connected in series, and 2^nd locking device.

EFFECT: higher noise immunity due to elimination of transient-process effects in control over launch and over launch leg that increase missile reliability and that of missile complex proper.

2 cl, 2 dwg

Description

The invention relates to the field of weapons, namely to rocket technology, and can be used in the development of missile systems, for example with carriers on the ground.

A known method of undermining a tandem warhead [RF patent No. 2233420 from 08.20.02, IPC ⁷ F42B 15/00], selected as a prototype. As follows from the description of the patent [p.6-8], the onboard equipment of the guided missile undermines the tandem warhead (warhead). At the same time, a method of undermining a tandem warhead is implemented, which consists in accumulating electric energy, which undermines the secondary and main warheads, and controls the undermining, respectively, of the first and second signals, while the second signal is delayed in time relative to the first.

Known guided missile in a transport and launch container [RF patent No. 2233420], which implements the known method, comprises a coil of a wireline, a steering drive unit with coils of control electromagnets, safety-actuating mechanisms of the main and additional warheads, and a time delay device to provide a delayed response the main warhead (warhead) is relatively additional, a voltage to DC converter has been introduced, a broken wire line between the rocket and the source of pos constant current of ground equipment and electrical energy storage of safety-actuating mechanisms and time delay devices, while the inputs of all electric energy storage devices are connected through a disconnected wire line to the battery of the transport launch container, as well as to the output of the voltage converter, the input of which is connected to one of the coils of the control electromagnets of the steering unit, and the coils of the control electromagnets are interconnected and with the output of the coil of the wire line , the input of which is connected through a transport-launch container with ground control equipment.

As follows from the foregoing, a known guided missile in a transport and launch container contains a guided missile, a transport and launch container, and ground control equipment, which as a whole is a missile complex [Radio Control Basics, ed. Vejcela V.A. and Tipugina V.N. M .: Sov. Radio, 1973, p. 31, Fig. 11.11].

In addition, given that the safety-actuating mechanisms of the main and additional warheads are (each) in series connected to an electric detonator and an energy storage device (for example, a resistor and a capacitor connected in series), they are named hereinafter, which corresponds to their function. Similarly, a time delay device (an electronic time delay device made in the form of a series-connected multivibrator and an electronic key) is hereinafter referred to as electronic delay.

A disadvantage of the known method and device is the low noise immunity of electronic delay due to transients during the control of the launch and at the launch site, which reduces the reliability of the rocket, and hence the missile system.

The objective of the present invention (method and device) is to increase the noise immunity of electronic delay by eliminating the influence of transients in controlling the launch and at the launch site, which increases the reliability of the rocket, and hence the missile system.

The problem is solved due to the fact that in the method of undermining a tandem warhead of a rocket, which includes accumulating electric power on a rocket from a ground power source through a disconnected wire line to undermine the additional and main warheads and controlling the time of explosions, respectively, of the first and second pulse signals, while the second pulse signal is delayed in time relative to the first, in addition, from the ground power source, the electric power supplied to the rocket through the edge is used aemuyu wired communication link, to enable the two locking devices, prohibiting operation of the main warhead and since breakage wireline and until the removal of missiles at the required distance from the launcher to produce rocket self blocking signal for blocking the inclusion of these devices.

A missile system that implements a method of detonating a tandem warhead missile contains a ground control equipment and a missile in a transport and launch container with a battery for powering the ground control equipment, connected via an interrupted wire line to the inputs of three rocket power storage devices, the output of the first rocket power storage device being connected to the first input of the electric detonator of the main warhead, the second input of which is connected to the output of the electronic delay, the power input of which is connected to the first output in a missile electric energy storage device, wherein the output of the third electric energy storage device of the rocket is connected to the first input of the detonator of the additional warhead, the rocket is equipped with a contact sensor and an integrating circuit, and the electronic delay contains an input device, a first blocking device, a delayed pulse shaper, a second blocking device and an electronic key the output of which is the electronic delay output, wherein the input device and the first blocking device are connected in series Namely, the output of the first blocking device through the delayed pulse former is connected to the first input of the second blocking device, which is connected to the electronic key control input by the output, the second input of the additional warhead electric detonator is connected to the electronic delay input device and connected to the output of the contact sensor, the first output of the second drive is connected with the input of the integrating circuit, the output of which is combined with the second output of the second energy storage device and is connected to the second inputs of first and second blocking devices.

The claimed method of undermining the tandem warhead is implemented as follows. Electric energy is accumulated on a rocket, for example, as in the prototype [patent No. 2233420], first from a ground-based power source for ground-based rocket control equipment through a disconnected wire communication line, and then (after it is broken), for example, from self-induction impulses of electromotive force (EMF) arising in the coils of the electromagnets of the rocket steering unit. The accumulated electric energy is used to undermine the additional (low-power) and main (powerful) warheads, and the first and second pulse signals are respectively controlled by the moments of undermining, while the second pulse signal is delayed in time relative to the first.

Additionally, electricity from a ground-based power source, supplied through a disconnected wire communication line, is used to turn on a lock that prohibits the operation of the main warhead. In this case, you can directly apply the voltage value of the power source, which represents a single logical level for logical digital circuits, or convert it to a zero logic level (or a signal close in magnitude to it). Since the absence of an electrical signal in a wireline, i.e. from the moment of its breakdown at the launch of the rocket and its removal to the required, for example, safe distance from the launcher (from the control point), an autonomous blocking signal is generated on the rocket.

The invention is illustrated in FIGS. 1 and 2. FIG. 1 shows a structural electrical diagram of a missile system that implements the claimed method, where 1 is a ground control equipment (NAU), 2 is a transport-launch container (TPK), 3 is a battery located in transport and launch container (B), 4 - disconnected wire communication line (PLC), 5a, 5b and 5c - first, second and third electric energy storage devices (respectively, NE1, NE2 and NEZ), 6 - contact sensor (CD), 7 - integrating circuit (IC), 8 - electronic delay (EZ), 9 - main detonator th bp (EDO), 10 - electric detonator additional warhead (EDD), 11 - input device (VU), 12a and 12b - the first and second blocking devices (BU1 and BU2), 13 - delayed pulse shaper (FZI), 14 - electronic key ( EC)

In Fig.1, the second conclusions on the power supply of the elements and blocks 1, 3, 4, 5a, 5b, 5c, 6, 7 and 8 are connected, for example, with the housing.

Figure 2 shows, by way of example, a circuit diagram of a second energy storage device 5b and an integrating circuit 7, where R1 and R2 are resistors, D1 is a zener diode, C1 and C2 are capacitors.

The claimed method includes a battery 3, which feeds the ground control equipment 1. The battery 3 is connected through the disconnected wire communication line 4 to the inputs of the first 5a, second 5b, and third 5c electric power storage devices. The output of the first energy storage device 5a is connected to the first input of the electric detonator of the main warhead 9, the second input of which is connected to the output of the electronic delay 8, the power input of which is connected to the first output of the second energy storage device 5b. The output of the third electric energy storage device 5c is connected to the first input of the electric detonator of an additional warhead 10, the second input of which is connected to the input of the input device 11 and the output of the contact sensor 6. The output of the input device 11 is connected to the first input of the first blocking device 12a, the output of which is connected via the delayed pulse former 13 with the first input of the second blocking device 12b. The output of the second locking device 12b is connected to the control input of the electronic key 14. The first output of the second energy storage device 5b is connected to the input of the integrating circuit 7, the output of which is connected to the second inputs of both locking devices 12a, 12b and to the second output of the second electricity storage device 5b.

Examples of the second energy storage device 5b and the integrating circuit 7 are shown in figure 2. Ground control equipment 1, a transport and launch container 2, in which a rocket is located prior to launch, a battery 3 located in the transport and launch container 2, the first 5a and third 5b electric power storage devices and an electronic key 14 are similar to the prototype. The electric detonators of the main warhead 9 and additional 10 are part of the safety-actuating mechanisms for detonating, respectively, the main and additional warheads shown in the prototype, and perform the same function. The driver of the delayed pulse 13 can be performed as a standby multivibrator in the same way as in the prototype.

The contact sensor 6 can be performed as the head contacts of the rocket, closed when the target is touched. The first 12a and second 12b blocking devices can be implemented as the first and second two-input logic circuit “And”. The input device 11 can be made in the form of an electronic key, the output signal of which, for example, a logic level, changes when the contact sensor 6 is triggered.

A missile system that implements a method of undermining a tandem warhead works as follows. At the initial moment of time (before launch), the rocket is located in the transport and launch container 2 and is connected by a wire line to the ground control equipment 1. At the time of launch, the battery 3 located in the transport and launch container 2 is turned on and energizes the ground control equipment 1, and also through the cut off (cut off) wire line of wire communication, power storage devices 5a, 5b and 5c, placed on the rocket.

Electric power storage devices 5a, 5b and 5c have a small time constant for charging and at the time of start, before the breakdown of the wireline, they manage to accumulate a sufficient amount of electricity, which can then be replenished, for example, as in the prototype.

As follows from figure 2, the second electric energy storage device 5b is supplied with voltage from the battery 3 through a broken wire communication line 4, which may contain one wire connected to the terminal, for example, minus the battery in the presence of a common (case) terminal, which is a plus of the battery, or contain two wires (in the absence of case). In connection with the above, a specific connection is not shown in figure 1. Two other drives are connected in the same way. Zener diode D1 stabilizes the voltage supplied from battery 4, and resistor R1 limits the amount of current flowing through the zener diode. The capacitor C1, which is the drive, is charged from the voltage at the zener diode D1 through the diode D2. In the presence of a wired communication line 4, the voltage across the capacitor C2 (at terminal 1 relative to terminal 2) is negative and is equal to the voltage drop across the diode D2.

If the wire communication line 4 is cut off, no current will flow through the diode D2 and capacitor C1 will begin to charge capacitor C2 through resistor R2, while the voltage across it will become positive and will increase to a voltage close to that on capacitor C1.

Therefore, the voltage value from the output of the integrating circuit 7 (from the capacitor C2) supplied to the second inputs of the first 12a and second 12b blocking devices, initially from the moment the voltage is supplied to the rocket and until the wire line breaks (when the capacitor C2 is shorted by the diode D2), and then, at the initial moment of charge of the capacitor C2 from the capacitor C1 (when the wire line is broken), it corresponds to a zero logic level, and as the capacitor C2 charges further, to a single logical level.

If necessary, the negative value of the voltage across the capacitor C2 can be eliminated, for example by including in the open circuit between the terminal 1 of the capacitor C2 and the second input of the blocking devices 12a and 12b in the forward direction, an additional diode loaded on an additional resistor, the second terminal of which is connected to the second output of the capacitor C2.

Thus, from the moment the battery 3 is turned on, the output of the integrating circuit 7 forms a zero logic level, which is fed to the second input of the first blocking device 12a and prevents the pulse from passing from its first input to the input of the delayed pulse former 13. The same logic level is fed to the second input the second blocking device 12b and prohibits the passage of the pulse from its first input to the control input of the electronic key 14. The causes of premature pulses arriving at the first moves the locking devices 12a and 12b may be transients in electronic delay 8, the voltage value jumps in wireline 4, for example, when triggered pyro, igniting the rocket booster engine (which may cause a momentary battery podkorotku) etc.

When the rocket is removed to the required distance from the control point, an integrated logic level is formed at the output of the integrating circuit 7, which is fed to the second inputs of the blocking devices 12a and 12b and allows the passage of the pulse to undermine the main warhead. At the moment of contacting the target sensor 6, it closes and connects to the housing an additional detonator БЧ 10, the second output of which is supplied with voltage from the third energy storage device 5v, and the additional detonator БЧ 10 is activated.

When the contact sensor 6 is closed, an output is generated at the output of the input device 11 with a single logic level, which is fed to the first input of the blocking device 12a. Since there is a single logic level at the second input of the blocking device 12a, this pulse passes to the input of the delayed pulse former 13 and generates a delayed pulse at its output. This delayed pulse enters the first input of the second blocking device 12b and likewise passes to its output and enters the control input of the electronic key 14. The electronic key 14 closes the output of the electric detonator 9, for example, to the housing and connects the first energy storage device 5a (through the housing output) to electric detonator main warhead 9, which leads to its operation.

Therefore, the proposed group of inventions, the method of undermining the tandem warhead and the missile system can increase the noise immunity of the electronic delay by eliminating the passage of interference caused by transients when controlling the launch and at the launch site, which increases the reliability of the rocket, and hence the missile complex.

Claims (2)

1. A method of detonating a tandem warhead of a rocket, comprising accumulating electric power on a rocket from a ground-based power source through a broken wire communication line to undermine the additional and main warheads and controlling the time of explosions by the first and second pulse signals, respectively, while the second pulse signal is delayed in time with respect to the first, characterized in that in addition to the ground power source, they use electric energy supplied to the rocket through a disconnected wire communication line and, to turn on two blocking devices that prohibit the operation of the main warhead, and from the moment the wireline is cut off until the rocket is removed to the required distance from the launcher, an autonomous blocking signal is generated on the rocket to turn on these blocking devices. 2. A missile system comprising a ground control equipment and a rocket in a transport and launch container with a battery for powering the ground control equipment, connected via a broken wire line to the inputs of three rocket power storage devices, the output of the first rocket power storage device being connected to the first input of the main combat detonator parts, the second input of which is connected to the output of the electronic delay, the power input of which is connected to the first output of the second energy storage of the rocket, pr the output of the third electric power storage of the rocket is connected to the first input of the detonator of the additional warhead, characterized in that the rocket is equipped with a contact sensor and an integrating circuit, and the electronic delay contains an input device, a first blocking device, a delayed pulse shaper, a second blocking device and an electronic key, output which is the electronic delay output, while the input device and the first blocking device are connected in series, the output of the first block the dimming device through the delayed pulse former is connected to the first input of the second blocking device, connected by the output to the control input of the electronic key, the second input of the detonator of the additional warhead is connected to the input device of the electronic delay and connected to the output of the contact sensor, the first output of the second drive is connected to the input of the integrating circuit the output of which is combined with the second output of the second energy storage device and is connected to the second inputs of the first and second blocks uyuschih devices.

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