RU2301960C2 - Safety-actuating mechanism for warheads of rocket ammunition - Google Patents

Abstract

FIELD: technical devices for equipment of ammunition warheads with an on-board power source, mainly of guided rockets or missiles having of cruise engine.

SUBSTANCE: the safety-actuating mechanism is characterized by the fact that it has a double-acting electrical detonator for equipment of the main detonator of the ammunition warhead, firing arming system, standard fitting system, self-destruction system and a system of protection at non-standard situations. The self-destruction system has an inertia starting mechanism, electric igniter, pyrotechnical self-destruction track, primer cap and a burned-through gasket, and the system of protection at non-standard situations has a shutter, contact coupled to it, shunting double-acting electrical detonator and an inertia mechanism.

EFFECT: enhanced reliability and safety of operation of the ammunition in standard and non-standard conditions.

3 cl, 5 dwg

Description

The invention relates to technical devices for engaging the warheads of ammunition with an onboard power source, mainly guided missiles or shells having a marching rocket engine.

The problem solved by the invention is to increase the reliability and safety of ammunition in normal and emergency modes.

The essential features of the invention (safety-executive mechanism - PIM) are: - the presence of an on-board power supply (BIP), connected to the PIM only after the munition is launched; - the presence of a double-action electric detonator (ED-DD), designed to engage the main detonator of the warhead of the munition; - equipping with systems of combat cocking, full-time engagement, self-liquidation and protection in emergency situations.

The essential features of a self-liquidation system are the presence of: - an inertial trigger; - electric igniter; - pyrotechnic self-destruction track; - igniter capsule; - burnable gasket protecting the ignition hole ED-DD from the penetration of hot gases of pyrotechnic compositions.

Essential features of the emergency protection system are the presence of: - shutters; - contact bypass ED-DD and associated with the valve; - inertial blocking mechanism.

A combat cocking system consists of: - an inertial trigger; - electric igniter; - an electrocapacitor charged from a BIP after start-up; - dampers with pyrotechnic delay of the cocking time; - inertial locking mechanism of the shutter.

The full-time activation system consists of: - an inertial target sensor; - electrocapacitor; - ED-DD.

Causal relationships between the essential features of the claimed invention and the mechanism for obtaining a technical result are described in the section "implementation of the invention".

Figure 1 shows an electrical diagram explaining the operation of the safety-actuating mechanism (PIM) in conjunction with other functional units of the munition (on the PIM wiring diagram is highlighted by a dashed line), in Fig. 2 is a design of the PIM in axial section, in Fig. 3 is a section A-A (according to the self-liquidation mechanism), Fig. 4 is a section along B-B (by an electric igniter, a long cocking mechanism and a lock), and Fig. 5 is a section along B-B (by a blocking mechanism).

The main detonator 1 of the munition (Fig. 1) is blown up by a double-action electric detonator (ED-DD) 2, capable of triggering both when voltage is applied to its electrical contacts 3, and from the force of the fire acting through the ignition hole 4. The last mode of operation in the claimed PIM is used for a self-liquidation system, and it is more reliable and safer than using an on-board power supply (BIP) for the same purpose, as is customary in well-known decisions, for example, US 5387257 of 02/07/1995 and US 6244184 of 06/12/2001. in well-known solutions we can It can be a consequence of the destruction of the BIP or electrical wiring in combat conditions. To ensure safety, electrical contacts 5 are provided for shunting the ED-DD 2 and guaranteeing its non-operation (even if the voltage is applied to the contacts 3 accidentally) until the long-range cocking mechanism trips and the bypass contacts open 5. BIP pos.6 begins to function at the time of launch and is connected to the circuit by the contactor 7 only after the ammunition leaves the container or barrel. The last two factors associated with the elements pos. 5 and 7 also contribute to increased safety in official handling. The electric capacitor 8 starts to charge through the resistor 9 and accumulates enough energy to trigger the ED-DD 2 even in the event of a malfunction of the BIP 6. Under the influence of the starting overloads of the munition, the inertial starting mechanism is activated, its contacts 10 are closed, the electric igniter 11 is activated, which starts for work of all pyrotechnic devices. The resistor 12 ensures that there is no short circuit in the BIP 6 during an abnormal short circuit between the input contacts 13 of the electric igniter 11 after it is triggered. Normal operation ED-DD 2 can occur when the contacts 14 of the inertial target sensor are closed or when the contacts 15 located on the munition body are closed. To ensure the safety of the ammunition at the time of launch when the contacts 14 or 15 are accidentally closed, a resistor 9 is used, which is selected so that the current flowing through it is less than the safe operation current of the ED-DD 2 and so that it charges the electric capacitor 8 to a long-range cocking.

One of the components of the combat cocking system is the shutter 16 (figure 2), mechanically preventing the transmission of the detonation pulse from ED-DD 2 to the main detonator 1 until the completion of the cocking process. The triggered electric igniter 11 (Fig. 4) ignites the pyrotechnic compositions 17, which burn out after a long cocking time, the stopper 18 rises under the influence of the spring 19 and the shutter 16 moves to the firing position, removing the last protection stage of the PIM. The locking mechanism is inertial, its rod 20 (Fig. 5) can block the shutter 16 with a pin 21 only during that period when the rocket engine is not working. The latter, during operation, constantly creates acceleration, under the influence of which the rod 20 settles, compressing the spring 22, the pin 21 is lowered and allows the shutter 16 to move after the spring 23 is lifted under the influence of the spring 23 into the fighting position (suspension) and be fixed there by the stop 24 when the spring 25 is applied. If the inertial overload acting on the rod 20 is short-term (abnormal), for example, when the ammunition falls from a high height or after starting up to the long-range cocking distance, the shutter 16 will still be held by the stopper 18, and the pin 21 will rise again and block the shutter 16. In this way, the task of increasing safety in official handling is solved in one of the possible emergency situations.

Simultaneously with the ignition of the pyrotechnic compositions 17 when the electric igniter 11 is triggered, the pyrotechnic self-liquidation track 26 (Fig. 3), ending in the igniter capsule 27 (Fig. 2), lights up at its beginning. The latter is installed with the possibility of firing ED-DC 2 through the firing hole 4. Due to the fact that in a small volume of PIM there is a high pressure of hot gases from the simultaneous operation of pyrotechnic devices 11, 17 and 26, premature operation of ED-DD 2 can occur. to prevent premature (abnormal) activation according to the specified scheme, the input of the ignition hole 4 is protected by a gasket 28 made, for example, of cardboard or thick paper and burned when the igniter 27 is triggered. le burnout track pyrotechnic self-destruct 26 primer 27 will provide reliable self-destruction of the munition, regardless of the presence of faults in the wiring diagram.

If all PIM devices are conventionally assigned to one of the systems, then their operation will be as follows:

- in the system of combat cocking, the elements 10, 11, 8, 17, 18, 20, 16, 24, 25, 5 are sequentially triggered;

- in the system of regular engagement, the sequential operation of elements 14 or 15, 8, 2, 1 occurs;

- the elements 10, 11, 26, 27, 28, 4, 2, 1 participate in the self-liquidation system;

- elements 16, 20, 21, 5, 28 are involved in the emergency protection system.

The advantage of the claimed design of the PIM is the high reliability of operation from the self-destruction mechanism due to the igniter capsule installed at the end of the pyrotechnic self-destruction track. Among other factors, the safety of PIM is also facilitated by an obturating pad, which protects the ED-DD inlet from penetration of hot gases of an electric igniter and other pyrotechnic compositions.

Claims (3)

1. A safety-executive mechanism for the warheads of missile ammunition, comprising an onboard power supply capable of connecting to it after launch, a double-action electric detonator to engage the main detonator of the warhead of the ammunition, a combat cocking system, a standard engagement system, a self-liquidation system and a safety system for emergency situations, characterized in that the self-liquidation system contains an inertial trigger, an electric igniter, a pyrotechnic the self-liquidation path, the igniter capsule and the gasket burned, and the emergency protection system includes a damper, a contact associated with it, a double-acting shunt electric detonator and an inertial blocking mechanism. 2. The safety-executive mechanism according to claim 1, characterized in that the combat cocking system consists of an inertial trigger, an electric igniter, an electric capacitor charged from the onboard power source after start-up, a damper with a pyrotechnic delay of the long-range cocking and with an inertial locking mechanism. 3. The safety-actuating mechanism according to claim 1, characterized in that the standard engagement system consists of an inertial target sensor, an electric capacitor and a double-acting electric detonator.

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