RU226910U1 - FIRE EXTINGUISHING ROCKET - Google Patents

Abstract

The utility model relates to the field of fire extinguishing, to devices that generate gas-aerosol combustion inhibitors, formed during the combustion of an aerosol-generating composition and directed in an organized manner, including to remote and hard-to-reach places, including high-rise buildings. The device contains a rocket engine housing (1), a gas duct (2), a charge of solid rocket fuel (3), a charge of an aerosol-generating (fire extinguishing) composition (4), a shank (5), a thermal insulation coating (TIC) (6), a fairing with gas exhaust holes (7), nozzle (8). The jet part is equipped with a heat-shielding coating (6) to protect the body (1) during operation and a shank (5) to stabilize the product during flight. 4 salary f-ly, 1 ill.

Description

The proposed utility model relates to the field of fire extinguishing, to devices that generate gas-aerosol flame retardants formed during the combustion of an aerosol-generating composition and directed in an organized manner into the protected volume, and can be used to extinguish fires in remote and hard-to-reach places, including in high-rise buildings in which Fire equipment is difficult to deliver to the fire zone on time.

In Pat. RU 2744324, IPC A62S 3/02, publ. 03/05/2021, a cassette for extinguishing a fire is presented, including a housing, a bursting charge, fire extinguishing powder, a fuse and a reactive part, while the cassette body has three parts. In the main part there is a container with outlet holes and a fire extinguishing agent contained in it under pressure. The housing also contains the head part of the cassette, containing a distance sensor with a battery, and a parachute system. The disadvantages of this scheme are that the container with the fire extinguishing agent is constantly under pressure. The cassette is intended only for parachute descent.

A method of extinguishing fires has been patented (Pat. RU 2182026, IPC A62S 3/02, published on May 10, 2002), which consists of suppressing combustion processes by exposing the fire source to a directed high-speed jet of fire extinguishing aerosol, formed during the throwing, ignition and combustion of an aerosol-generating composition in flight. The aerosol-generating composition is thrown from any flamethrower, including a backpack one, and from an ampoule flamethrower the composition is thrown in a grenade ampoule. The design of the ampoule-grenade has not been disclosed.

In Pat. RU 2403930, IPC A62С13/00, publ. 11/20/2010, a design is presented designed for volumetric fire extinguishing in confined spaces by manually throwing the device into the fire. The gas-aerosol mixture is generated during the combustion of pyrotechnic charges.

The design of a utility model device is known according to patent RU 137958, IPC A62C 35/00, publ. 02/27/2014. The aerosol fire extinguishing device is designed for operation in stationary conditions. Includes housing, ablative lining, aerosol-forming composition charge, igniter, nozzle, diaphragm. The main disadvantage of the device is that it is stationary.

The design of a rocket is known (Utility model RU 49976, IPC F42D5/04, publ. 12/10/2005), consisting of a carrier, a warhead, docked with the rocket using a joint. A capsule is installed as a payload (instead of a removed warhead) to extinguish fires in remote, hard-to-reach areas. The capsule contains a sealed chamber filled with a working fluid, for example, liquid propane. A detonating extended charge (EDC) of a cumulative type, a detonator and an igniter are installed on the outer surface of the chamber. Disadvantages: during the operation of this device, an explosion occurs, destruction around the extinguishing site is possible, and loss of life due to fragments of the body is possible.

The closest in essence to the proposed technical solution is the design of the device in the form of a fire-fighting rocket-propelled grenade, which includes a body, an explosive charge, fire extinguishing powder, a fuse and a reactive part. The body is made in the form of cylindrical cones connected by bases. Using a threaded fastening, the tail part of the body is attached to the reactive part, and the nose part of the body is attached to the fuse (Pat. RU 2442624, IPC A62S 3/02, publ. 02.20.2012). The fire extinguishing powder, which is a phosphorammonium salt, is laid evenly throughout the body, around the explosive charge until it is completely filled. The reactive part is a metal cylinder with a tail, a nozzle and a starting charge with the ability to impart initial acceleration to a fire-fighting rocket-propelled grenade and throw it into the extinguishing zone.

The disadvantage of the device chosen as a prototype is the limited effectiveness of fire extinguishing, due to the difficulty of accurately entering high-rise buildings and the use of phosphorammonium salt fire extinguishing powder. The presence of a fuse determines the danger and design complexity of the device. Destruction around the extinguishing site and loss of life due to fragments of the hull are possible.

The problem that the utility model is aimed at is to improve the safety of fire fighting equipment in remote and hard-to-reach places, including high-rise buildings, and to simplify and safety the use of fire extinguishing devices.

A fire extinguishing rocket design has been proposed, intended for extinguishing fires in remote and hard-to-reach places, including high-rise buildings, containing a housing, a combustion chamber with a fire extinguishing agent placed in it and a reactive part, in which a charge of an aerosol-generating composition is used as a fire extinguishing agent, and the system for activating the aerosol-generating composition charge is a propellant charge (RT) or a rocket fuel charge and an aerosol-generating composition charge. In this case, the head part of the rocket is made with the ability to overcome the integrity of an obstacle encountered on the path of the rocket's flight, in the form of a fairing with gas outlet holes and is associated with a gas duct.

In the preferred embodiment, a composition with a low (less than or equal to 2700K) temperature of combustion products is used as a rocket fuel charge.

Depending on the distance to the target, the mass of the rocket fuel charge, which determines the distance of the active part of the flight, varies.

The charge of the reactive part, depending on the task at hand, can be a charge of rocket fuel or a combined charge of RT with an aerosol-generating component in its composition.

The mass ratio between the charge of rocket fuel and the charge of the aerosol-generating composition depends on the distance to the source of fire and the combustion area. In a preferred embodiment, the ratio between the mass of the aerosol-generating charge and the mass of the propellant charge is from 1:0.5 to 1:10.

A tip made of hard material (HRC≥50) or another device may be additionally located in the missile head to disrupt the integrity of an obstacle (surface) encountered on the missile’s flight path.

The proposed rocket design uses a propellant charge to deliver fire extinguishing agent to the source of the fire. Low-temperature combustion products increase the safety of using a fire extinguishing rocket. After the product enters the combustion zone from a certain distance without the use of additional equipment, uniform fire extinguishing begins with the help of an aerosol-generating composition.

In fig. The proposed design of a fire extinguishing rocket is shown (longitudinal section). The device contains a rocket engine housing (1), a gas duct (2), a rocket fuel charge (3), an aerosol-generating (fire extinguishing) composition charge (4), a shank (5), a thermal insulation coating (TIC) (6), a fairing with gas exhaust holes ( 7), nozzle (8).

The gas duct (2) ensures the outflow of the aerosol-generating composition through the holes of the fairing (7), balancing the outflow through the nozzle (8) and contributes to the uniform distribution of the aerosol-generating composition over the combustion area.

The rocket engine is equipped with a heat shield (6) to protect the body (1) during operation and a shank (5) to stabilize the product during flight.

The operation of the proposed device: a fire extinguishing rocket is attached to an unmanned aerial vehicle with a surveillance camera and an aiming system. It is possible to install the rocket on a manual launcher with any type of sight. The operator, using a surveillance camera (sight), aims the fire extinguishing rocket at the target and launches the rocket fuel charge (3) by applying an electrical impulse to the igniter placed in the rocket nozzle (8). Entering the fire zone from a given distance, the rocket begins to emit a fire-extinguishing aerosol from the charge (4), first through the nozzle (8), and then through the gas outlet holes (7), which makes it possible to effectively and uniformly extinguish the fire. To eliminate fires of various sizes, it is possible to use rockets of different calibers.

Technical effect: the design of the rocket, using a charge of rocket fuel to deliver an aerosol-generating composition to the source of fire, especially to remote and hard-to-reach places, including high-rise buildings, is simple to implement, requiring only launch at the source of fire (no other devices are used after launch , fuses, etc.). The rocket in use does not cause destruction around itself (there are no explosives, no shock wave). The rocket body remains intact.

Claims (5)

1. A fire extinguishing rocket containing a body, a combustion chamber with a fire extinguishing agent placed in it and a nozzle part, characterized in that a charge of an aerosol-generating composition is used as a fire extinguishing agent, and the system for triggering the charge of an aerosol-generating composition is made in the form of a charge of rocket fuel, while the head part of the rocket in the form of a fairing with gas exhaust holes and associated with the gas duct is designed to overcome the integrity of an obstacle encountered on the rocket's flight path. 2. The rocket according to claim 1, characterized in that a composition with a low temperature of combustion products is used as a rocket fuel charge. 3. The rocket according to claim 1, characterized in that the mass ratio between the charge of rocket fuel and the charge of the aerosol-generating composition is selected depending on the distance to the source of fire and the combustion area. 4. The rocket according to claim 1 or 3, characterized in that the ratio between the mass of the aerosol-generating charge and the mass of the rocket fuel charge is from 1:0.5 to 1:10. 5. The rocket according to claim 1, characterized in that in its head part there is additionally a tip made of solid material or a device for violating the integrity of an obstacle encountered on the rocket’s flight path.

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