RU49976U1 - MISSILES TO BE DISPOSED AND CAPSULE FOR FIRE FIGHTING - Google Patents

Abstract

The utility model relates to the field of rocketry and can be used to dispose of decommissioned missiles, primarily for tactical purposes, as well as to extinguish fires in remote, inaccessible areas. On a rocket taken out of service, the combat unit is replaced by a capsule for extinguishing a fire, which is filled with a working fluid, for example, liquid propane. Before using the capsule in the fire, liquid propane is transferred to a gaseous state using a gas generator. The capsule delivered by the rocket to the fire site, on command from the rocket control system, opens like shell flaps using a detonating elongated charge mounted on the outer surface of the capsule in the form of an open loop. When the capsule opens immediately, gaseous propane burns out, and an oxygen-free zone is created in the fire. Thus, the rocket is simultaneously utilized and the fire is extinguished in a remote inaccessible area.

Description

The utility model relates to the field of rocketry and can be used to dispose of decommissioned missiles, primarily for tactical purposes, as well as to the field of extinguishing large-scale fires in remote, inaccessible areas.

At present, both in Russia and abroad, the missiles to be disposed of are disassembled into components at special industrial bases where fuel is drained, its residues neutralized, disassembled into component parts, reprocessing and subsequent destruction of component parts. The greatest difficulty is the disposal of solid rockets, because in a solid-propellant rocket, in addition to the hull, a solid-fuel charge is cut off and destroyed (see, for example, RF patent No. 2143660 with priority of 04/28/98). In this invention, the disposal of missiles is carried out by disassembling the missiles, hydro-cutting charge, its subsequent grinding and burning in a special furnace. All this requires the adoption of special measures to ensure the safety of work, large-scale construction of recycling facilities, high financial costs. The technological cycle for the disposal of missiles taken out of service at industrial bases is quite long, the capacity of the bases is limited,

which significantly reduces the efficiency of disposal.

There is also a known method for the operational elimination of missiles (see Rocket and Space Technology No. 25, 26 of 06.24.1988) by direct shooting, which is not financially justified.

The rocket to be eliminated is also known (see RF patent No. 2139491 with priority dated July 27, 98), in which data are entered into the flight mission of the rocket that ensures at a given point in time that the permissible deviations of the rocket from the standard trajectory are exceeded, which triggers the emergency rocket self-destruction system .

Utilization of regular missiles by direct launches without their additional conversion to perform other useful functions is a very expensive undertaking.

The objective of this utility model is to eliminate the above drawbacks and obtain a technical result consisting in using missiles removed from combat duty as delivery vehicles to remote and remote (over hundreds and thousands of kilometers) areas of fire extinguishing devices installed instead of a combat charge, creating hotbed of a zone of deep oxygen deficiency.

Thus, the missile to be disposed of is simultaneously destroyed and the fire is extinguished in hard-to-reach and remote areas in a short time.

A device for extinguishing large-scale forest fires is known, comprising a sealed chamber with liquid propane, a fuel nozzle, a heating element representing a charge of solid fuel ignited on command, a steam exhaust system and a Laval nozzle (see description to copyright certificate No. 1496804 with priority dated 17.07 .87).

The specified device allows in the shortest possible time to create an oxygen-free zone in the fire due to the rapid burning of oxygen during the interaction of vaporous propane with a flame in the fire. Despite the high fire extinguishing efficiency, this device has several disadvantages:

- problematic is the ground-based delivery of the device to a remote and remote fire (over several thousand kilometers);

- requires a special device to parry the jet pulse generated by the expiration of propane vapor through the Laval nozzle;

- the work of the fire crew operating the device in conditions of oxygen deficiency is problematic;

- the inability to use the device when fighting a fire in remote and inaccessible areas by dumping from an airplane, helicopter, airship, because when propane vapors are released through a Laval nozzle, it turns into an uncontrolled jet engine with an unpredictable flight path.

A device is also known for extinguishing fires in remote and inaccessible areas (see Utility Model Patent No. 4158 with priority dated June 16, 2004), which contains a sealed chamber with a working fluid, for example propane, a gas valve, a heating element, an activation system that detonates an elongated charge (ДУЗ) cumulative type with a detonator and an igniter. The specified device is also equipped with a protection mechanism against unauthorized operation of remote sensing devices.

Despite the obvious advantages compared with the above technical solution in the utility model (patent No. 41258), two simultaneously triggered remote sensing devices are installed to exclude the expansion of fragments on the outer surface of the camera

on an arc with an angle α, which complicates the process of opening the camera, because the opening of the camera parts takes place along an arc not destroyed by the remote sensing system, which does not exclude the appearance of fragments.

The objective of the proposed utility model is to create a device that simplifies the process of opening a capsule to extinguish a fire and eliminating the expansion of fragments.

This technical result is achieved by the fact that the DPS is installed in a plane passing through the axis of rotation of the capsule and the poles of the bottoms, and is fixed in the form of an open loop on the outer surfaces of the bottoms and one of the generators of the chamber on a straight section between the bottoms.

The proposed utility model allows you to quickly deliver a capsule to extinguish a fire in a remote and inaccessible area with a missile, the coordinates of the fire center are entered in the flight task, eliminate the missile for the benefit of the national economy, and eliminate the spread of fragments after opening the capsule.

This eliminates the need for fire brigades to be in the fire.

The essence of the utility model is illustrated by graphic materials, where

figure 1 shows a General view of a rocket with a capsule installed in it to extinguish a fire;

figure 2 shows a capsule for extinguishing a fire;

figure 3 is a section aa in figure 2 (shows the installation of remote sensing);

figure 4 is a section bB in figure 3.

The missile to be disposed of (Fig. 1) consists of a carrier 1, a head part 2, docked with a missile using

junction 3. As a payload 4 (instead of a removed warhead), a capsule 5 is installed to extinguish a fire in remote, inaccessible areas. The carrier can be one-, two- and three-stage, both on liquid and on solid fuel. The capsule 5 (figure 2) contains a sealed chamber 6, filled with a working fluid 7, for example liquid propane. The chamber 6 is filled with liquid propane through a filling valve 8. The working fluid is transferred from a liquid to a gaseous state by a heating element 9 mounted in the chamber 6, which can be made in the form of a solid fuel gas generator, activated by a command at a specified time. On the outer surface 10 of the chamber 6 (Fig.2, 3, 4) installed detonating elongated charge (DLD) 11 of the cumulative type, the detonator 12 and the ignitor 13.

In order to prevent unauthorized operation of the remote sensing device on the outer surface 10 of the chamber 6 (see Fig. 4), a safety mechanism 14 is mounted with a pyro cartridge 15 and a piston 16 that overlaps the fire channel 17 in the initial position between the detonator 12 and the igniter 13.

Depending on the design of the head part 2, the sealed chamber 6 of the capsule 5 can be made in the form of a body of revolution, for example, a truncated cone 18 with hemispherical bottoms 19 and 20. Other chamber manufacturing options are possible: ball, cylinder with bottoms, etc. The material of the chamber 6 is a light alloy or composite material.

In order to exclude the expansion of fragments after opening the capsule and simplify its disclosure, DUZ 11 is installed (see Fig. 3) in a plane passing through the axis of rotation of the capsule and the poles 21 and 22 of the bottoms and fixed to external surfaces

bottoms and one of the generators of the cone in a straight section between the bottoms 19 and 20 in the form of an open loop. The operation of the heating element 9, the igniter 13, the squib 15 is carried out on command from the missile control system.

The utility model works as follows. On the rocket to be disposed of, instead of a warhead, a capsule 5 is installed to extinguish fires in remote, inaccessible areas. The capsule is filled with a liquid working fluid 7, for example propane, through a filling valve 8 to 70-80% of its volume.

The missile is mounted on fire watch and is in standby mode for a signal from the satellite Earth monitoring system. In the event of a fire, the coordinates of the fire center are entered into the missile’s flight mission and the rocket is launched into a given remote (many hundreds and thousands of kilometers) and inaccessible area.

Before dropping the capsule in the fire from the missile control system, a command is sent to the heating element 9, with which propane is heated to a temperature of 80-100 ° C and from a liquid state passes into a gaseous state in 20-100 sec, while the pressure in the chamber rises to 100 -150 kg / cm ² . Then, a command is issued to the igniter 15 of the safety mechanism 14, after which the piston 16 releases the fire channel 17 under the influence of gases. After giving the command to the ignitor 13, a remote sensing device 11 is initiated from the detonator 12, and due to the cumulative effect, the chamber material under the remote sensing is destroyed, and the opening of the chamber 6 due to the high pressure created in the chamber 6. DUZ laid in the form of an open loop, the halves open

chamber 6, similar to shell flaps. Vapors of gaseous propane are instantly released and interact with the gas-air mixture in the fire, as a result of which a zone with a deep oxygen deficiency is created, which makes it possible to extinguish the fire in a short time. The rocket fuel burns out during its flight, and the remaining rocket is destroyed when it hits the ground.

Claims (2)

1. The missile to be disposed of, mainly for tactical purposes, containing a carrier, a head part with a payload and a control system, characterized in that the payload is made in the form of a capsule for extinguishing a fire in remote inaccessible areas, involved in a fire center on command from control systems. 2. A capsule for extinguishing a fire in remote, inaccessible places, placed in the head of a rocket, containing a sealed chamber made in the form of a body of revolution, for example, a truncated cone with hemispherical bottoms, and filled with a liquefied working fluid, such as propane, a gas valve, a detonating heating element elongated charge, a mechanism for protecting against unauthorized operation of a detonating elongated charge and a system for activating a heating element, a protection mechanism and a detonir an elongated charge, characterized in that the detonating elongated charge is installed in a plane passing through the axis of rotation of the capsule and the poles of the bottoms, and is fixed in the form of an open loop on the outer surfaces of the bottoms and one of the generators of the cone in the area between the bottoms, and the activation system is connected to the system rocket control.