RU2803986C1 - Fire protection device - Google Patents

Abstract

FIELD: fire-fighting equipment.

SUBSTANCE: invention relates to a fire-fighting device for creating a fire-fighting mineralized strip. The device contains a launcher (L), in which there is a container with a detonating cord (DC), enclosed in an elastic shell filled with granular fire extinguishing composition, equipped with an electric detonator, and a brake cable (BC), connected to the DC, which is equipped with a speed absorber and a solid propellant rocket engine (SPRE), the charge of which provides a continuous increase in thrust during operation and does not emit K-phase during combustion, while the SPRE is connected to the DC through a spring damper, and the SPRE itself is equipped with a stabilizer in the form of a cylinder covering the nozzle exit. The speed damper is formed by a part of the BC located on the launcher side, assembled in the form of one or more loops, intercepted by a tape with a tensile strength less than the tensile strength of the BC and DC, and the delay time for the operation of the electric detonator is greater than the operating time of the SPRE, and the control panel simultaneously sends commands to activate the SPRE initiator and the DC electric detonator.

EFFECT: invention ensures automatic delivery of a detonating cord with a granular extinguishing composition to the place where a firebreak is created using a solid fuel rocket engine, reducing time and increasing the accuracy of its placement, while eliminating the impact of combustion products of a solid fuel rocket engine on the surrounding area.

7 cl, 7 dwg, 1 tbl

Description

The invention relates to the field of environmental protection, namely to fire-fighting equipment that creates a fire-fighting mineralized strip.

There is a known method of extinguishing a fire (see patent RU No. 2144401), including a charge from a gas explosive mixture. The components of the mixture are delivered to the fire zone in solid form and they are filled into an elastic container. Then the detonation of the mixture is initiated, the products of which can be environmentally friendly. The shock wave extinguishes the fire. Delivery of components, equipment and their installation in a fire zone is a dangerous operation and also requires the use of special equipment and significant time to prepare the system for operation.

There is a known method of extinguishing fires (see RU patent No. 2700227) by exploding an explosive charge in the form of a piece of high-power detonating cord (DS) and containers with a fire extinguishing agent attached to it. The containers are made of plastic in the form of a hollow cylinder and have grooves for fastening the longwalls, and the lengths of the longwalls are overlapped and mounted in one or more lines. The disadvantage of this device is the operation of laying out and adjusting the location of the blast gun in the blast zone, which is performed manually and requires a significant amount of time.

Known mine clearance installations UR-77, URP-01 (see video "Russian Minesweeper UR77 Meteorite", Armies Power channel on YouTube.com, link https://www.youtube.com/watch?v=E_89Y-I8fPs), which are located on special vehicles or platforms designed to make passages in minefields, as well as a method of extinguishing fires (see RU patent No. 2193906) by exposing the source to an air shock wave and a dispersed cloud of extinguishing agent, in which rockets launched from from helicopters. These devices have the disadvantage that special equipment is required for their delivery, and they are also large in size and weight.

A device is known for delivering DP to the layout area using a powder jet engine (PRE). For example, the ZRP-2 device, adopted as a prototype (see the video “Trail Demining Charge in Action”, Crash Zone channel on YouTube.com, link https://www.youtube.com/watch?v=F_PPd0Ovkw8) , which is designed for clearing minefields. The device contains a launcher (PU) with a guide for the PRD, which is connected to the DS and the brake cable (TT), as well as the PU lock. The activation of the PRD and DS is carried out from the PU. The TT ensures delivery of the blast gun no further than the detonation zone. The disadvantage of this device is the operation of manually adjusting the layout of the thruster due to the fact that at the moment the thruster is completed and the thruster is fully selected from the launcher, the thruster is still on the flight path above ground level and has an excess force impulse necessary to achieve a given landing point PRD, as a result of which a reaction force arises that acts on the DU-DSH-TT system, due to which the DU-DSH-TT system receives movement in the opposite direction, which leads to a deviation of the system laying accuracy from a straight line and to additional time spent on adjustment DS layouts by pulling TT.

The objective of the proposed invention is to develop a device for creating a fire-fighting mineralized strip using a fire-resistant rocket with a reduced laying time and increasing the accuracy of laying it on the ground by automating the process, as well as eliminating the impact of combustion products of a solid propellant rocket engine (SFRM) on the surrounding area.

The problem is solved due to the fact that a fire-fighting device consisting of a launcher, in which there is a container with a diesel propeller, equipped with an electric detonator, a TT, which is connected to the launcher and propeller, and a solid propellant rocket motor with a charge coupled to the propeller mounted on the launcher guide, adjustable in direction and the angle of inclination, in turn, the electric detonator and the initiator of the solid propellant rocket engine are connected by electric cables to the control panel of the launcher, while the diesel shock is placed in an elastic shell filled with granular fire extinguishing composition, and the TT is equipped with a speed damper located on the side of the launcher, while the electric detonator is made with a delay response time. The solid propellant rocket motor is made with a charge that provides a continuous increase in thrust during operation of the solid propellant rocket motor and the solid propellant rocket motor contains ballistic fuel; in addition, the solid propellant rocket motor is coupled to a diesel propeller with a granular fire-extinguishing composition through a spring damper and is equipped with a stabilizer in the form of a cylinder covering the nozzle exit and secured to the body by pylons. The speed absorber is formed by a part of the TT, assembled into one or several loops, intercepted by a tape with a tensile strength less than the tensile strength of the TT and DS with granular fire extinguishing composition, and the delay time for the operation of the electric detonator is greater than the operating time of the solid propellant motor by 2...3 s.

The proposed technical solution is illustrated by drawings.

Fig. 1 - PU device.

Fig. 2 - Design of a fire extinguishing agent in an elastic shell with granular fire-extinguishing composition.

Fig. 3 - Design of the speed damper.

Fig. 4 - Solid propellant rocket motor devices.

Fig. 5 - Scheme for creating a mineralized firebreak.

Fig. 6 - Diagram of the speed damper before operation.

Fig. 7 - Diagram of the speed damper after activation.

The fire extinguishing device consists of a PU (1) containing a container (2) with a cylinder head (3), which is placed in an elastic shell (4) filled with a granular fire extinguishing composition (5) and equipped with an electric detonator (6), and is also connected to a TT (7 ). The TT (7) is equipped with a speed damper (8). There are many devices that act as a speed damper, such as devices using a lever, spring, electromagnet or electric motor, but these devices require the use of CT position sensors. In order to ensure reliability and for reasons of ease of execution, a speed damper circuit (8) was chosen, which consists of sections of the same cable in the form of loops (9), which are fixed in a static position with tape (10). CT (7) is connected to PU (1). On the guide (11) of the launcher (1) a solid propellant rocket motor (12) is installed, which consists of a charge (13) enclosed in a housing (14), a nozzle (15) and a stabilizer (16), fastened to the body by pylons (17). The solid propellant rocket engine (12) is connected to the diesel propeller (3) through a spring damper (18). The launcher (1) is equipped with a control panel (19) and is connected by electrical cables (20) to the electric detonator (6) and the solid propellant rocket motor (12).

The proposed device works as follows: the location of the protective strip, the installation location of the launcher and the orientation along the layout trajectory are determined. For precise placement of the DS with granular fire extinguishing composition, it is customary to move the DS with granular fire extinguishing composition along a flat trajectory with an inclination angle of the guides of ~3°. Depending on the terrain and the difference in heights of the launch site and the location of the landing gear with granular fire extinguishing composition, the angle of inclination of the guide is adjusted. At the remote command of the operator, the solid propellant rocket motor is started and the command to activate the electric detonator is made, after which the solid propellant rocket motor comes out of the guides and sequentially pulls the propeller motor with granular fire extinguishing agent and the TT, and the spring damper compensates for the load on the propeller motor with granular fire extinguishing agent at the start, and the thrust of the solid propellant rocket engine at the moment of start minimum to reduce loads and further increases in proportion to the increasing drawn out mass of the fire extinguishing agent with granular extinguishing composition. The electric detonator operates with a time delay, which is no less than the time from the moment the solid propellant rocket engine is launched until the complete deployment of the blast gun with granular fire-extinguishing composition. The stabilizer performs the functions of ensuring the stability of the solid propellant rocket engine in flight along the trajectory, while the thrust of the solid propellant rocket engine increases due to the formation of a second air circuit, which also reduces the temperature of the outer layers of the gas stream at the outlet of the nozzle, while the solid propellant rocket engine does not emit K-phase at the outlet when the charge is burned from the nozzle through the use of ballistic fuel. When the diesel engine with granular fire-extinguishing agent and the TT are fully drawn out, the length of which is determined from the safety conditions and the laying distance of the engine with granular fire-extinguishing agent, the solid propellant engine stops working, the speed damper is activated, which, when the tape fixing the 4-cylinder loop breaks, reduces the force impulse of the system, and the quantity loops ensure a reduction in the speed of movement of the system, which increases the accuracy of the layout of the diesel propeller with granular fire-extinguishing composition, while the ballistic trajectory is calculated in such a way that after the solid propellant rocket motor reaches the ground level, the diesel propeller with granular fire-extinguishing composition and the TT are located in one line over the full length, with a horizontal component speed is minimal. After the layout, the electric detonator is triggered, the delay time of which is greater than the operating time of the solid propellant rocket motor by 2...3 s, and the blast furnace with granular extinguishing composition is triggered and a fire-fighting mineralized strip is formed.

The characteristics of one of the options are shown in the table.

The use of the proposed technical solution will improve the efficiency of the process of creating a fire-fighting mineralized strip due to the use of blast furnaces with a granular fire-extinguishing composition with a reduced laying time, the accuracy of laying the blast furnace with a granular fire-extinguishing composition on the ground due to the automation of the process, and eliminate the impact of combustion products of solid propellant rocket engines and blast furnaces on the surrounding area.

Claims (7)

1. A fire-fighting device consisting of a launcher (PU), in which there is a container with a detonating cord (DS), equipped with an electric detonator, a brake cable (TT), which is connected to the launcher and DS, and a solid fuel rocket engine (SDTT) with a charge , docked with the DS and installed on the PU guide, adjustable in direction and angle of inclination, in turn, the electric detonator and the solid propellant initiator are connected by electrical cables to the PU control panel, characterized in that the DS is placed in an elastic shell filled with granular fire-extinguishing composition, and the TT is equipped a speed damper located on the PU side, while the electric detonator is designed with a response time delay. 2. The device according to claim 1, characterized in that the solid propellant rocket engine is made with a charge that provides a continuous increase in thrust when the solid propellant rocket engine is operating. 3. The device according to claim 1, characterized in that the solid propellant rocket engine contains ballistic fuel. 4. The device according to claim 1, characterized in that the solid propellant rocket engine is coupled to a diesel engine with granular fire extinguishing composition through a spring damper. 5. The device according to claim 1, characterized in that the solid propellant rocket engine is equipped with a stabilizer in the form of a cylinder covering the nozzle exit and secured to the body by pylons. 6. The device according to claim 1, characterized in that the speed absorber is formed by a part of the TP, assembled into one or more loops, intercepted by a tape with a tensile strength less than the tensile strength of the TP and DS with a granular fire extinguishing composition. 7. The device according to claim 1, characterized in that the delay time for the operation of the electric detonator is longer than the operating time of the solid propellant motor by 2...3 s.

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