RU2227888C1 - Missile launcher - Google Patents

Abstract

FIELD: rocketry, applicable in anti-ship missile complexes of above-water craft. SUBSTANCE: the launcher tube block is provided with a pipe-line of the outer sprinkling system. Each launching tube is provided with pipe-lines of inner sprinkling and chemical fire suppression, as well as with shutters of the thermostatting system. A drain valve is located in the rear part of each launching tube. The pipe-line of the outer sprinkling system may be provided over the entire length with rows of three holes symmetrically arranged on each side of the pipe-line every row of holes. The pipe-lines of inner sprinkling and chemical fire suppression may be installed on the outer side of the launching tube body and connected to the launching tube interior by spray and conical injectors respectively. The shutters may be made in the form of two aligned cylinders provided with lateral cut-outs coinciding with one another during operation of the thermostatting system and shut-off before missile launching. The discharge channel may have an actuator made in the form of a piston with a sheared member. EFFECT: provided storage on the ship of missiles requiring maintaining of a definite temperature condition in the launching tubes. 5 cl, 9 dwg

Description

The invention relates to rocket technology and can be used in anti-ship missile systems of surface ships.

Known launchers MK-140 and MK-141 missile complex "Harpoon" surface ships of the US Navy, consisting of a base mounted on the deck of the ship, which are installed removable transport and launch containers with cruise missiles (Gunner's Mate Ml & C, Naval education and training program development center US government printing office Washington, DC, 1979, p. 44 fig. 2-16).

Known launcher (patent No. 2172232 of June 10, 1997. Russian Federation F41F3 / 04), adopted as a prototype (see figure 1).

The launcher consists of bases made in the form of shock-absorbing supports 1, a removable frame 2 and transport-launch containers 3 with cruise missiles.

Such launchers provide storage of cruise missiles that do not have restrictions on storage temperature when they are on the ship. The disadvantage of launchers is the lack of a system for eliminating a possible fire of fuel when it is on the ship.

Cruise missiles are known, when in the launch tubes on the ship it is necessary to create certain temperature conditions in the launch tubes.

The aim of the present invention is the provision of storage on the ship of missiles that require maintaining a certain temperature in the launch tubes, as well as the elimination of emergency situations on the ship in case of possible ignition of the fuel of the rocket when it is in the launch tube.

This goal is achieved in that the missile launcher is made in the form of a block of launch tubes, consisting of at least two launch tubes, which is equipped with an external irrigation system, and each launch tube having longitudinal support beams is equipped with pipelines of internal irrigation and chemical extinguishing systems, moreover in the longitudinal support beams are placed thermostatic dampers, and a drain valve is located at the rear of each launch tube.

The presence of an external pipe irrigation system ensures that the temperature effect of solar radiation is removed from its outer surface, especially in areas with a tropical climate. The pipeline of the external irrigation system has along its entire length rows of three holes symmetrically located on each side of the pipeline through each row of holes, which ensures uniform distribution of water along the upper outer surface of the launch tube block.

The creation of a microclimate in the launch tube is ensured by the supply of air from the ship's air conditioner through the air ducts, which end in the launch tube by dampers. The dampers are located in the front and rear parts of the longitudinal support beams of the launch tube, through one of which air is supplied, and through the other air is aspirated. The placement of the dampers in the longitudinal support tanks eliminates the erosive effect of the mixed fuel jet of the rocket launch engine. In order to avoid excessive pressure from the jet of the rocket starting engine into the air ducts, which can lead to their destruction, the flaps before the rocket launch are automatically closed. Structurally, the shutters are made in the form of two coaxial cylinders with transverse cuts that coincide during the operation of the thermostatic control system, and overlap before launching the rocket by moving the internal cylinder.

In case of rocket fuel ignition while it is in the launch tube, the extinguishing is carried out in a complex manner - by supplying water through the internal irrigation system and extinguishing agent through the chemical extinguishing system. In order to avoid the erosive effect of the jet of the rocket launch engine on the pipelines of the systems, they are located outside the launch tubes. Pipelines are connected to the internal cavity of the launch tube by jet and conical type nozzles, respectively. Since the water and extinguishing agent are supplied to the launch tube until the fire is completely eliminated, and the internal cavity of the launch tube is sealed, a drain valve is provided at the rear of the pipe to drain excess water and extinguishing agent, which automatically opens when water and the extinguishing agent enter the internal cavity launch tube. Opening the piston of the drain valve is provided by triggering the shear element from the pressure created when the igniter is triggered.

The essence of the invention is illustrated by drawings, which depict:

figure 1 - launcher (patent No. 2117232, RF);

figure 2 is a General view of the proposed rocket launcher;

figure 3 - callout I in figure 2 (pipeline external irrigation);

figure 4 is a section bB in figure 3;

in Fig.5 is a view A in Fig.2 (launch tube with the rear cover removed);

figure 6 - section bb in figure 5 (pipeline internal irrigation);

in Fig.7 is a section GG in Fig.5 (chemical extinguishing pipeline);

in Fig.8 is a section DD in Fig.5 (shutter in the open position);

figure 9 - callout II in figure 5 (General view of the drain valve).

Missile launcher (see figure 2) consists of a block of pipes formed by two or four launch tubes 4, equipped with longitudinal support beams 5, which are placed shutters 6 of the temperature control system. An external irrigation system 7 is installed in the upper part of the pipe block.

On the outside of each launch pipe, internal irrigation systems (see Fig. 5) and chemical extinguishing systems 9 are installed, and a drain valve 10 is located at the rear of the launch pipe. Water is supplied from the internal irrigation system to the launch pipe through nozzles 11 (see Fig. 6) jet type, which ensures uniform distribution of water throughout the internal volume of the launch tube, and the extinguishing agent is supplied through nozzles 12 (see Fig. 7) of a conical type.

The valves of the temperature control system (see Fig. 8) consist of an outer cylinder 15 and an inner cylinder 16, in which transverse slots are made. In the open position, the slots coincide, and when moving the inner cylinder, it overlaps the slots of the outer cylinder, which eliminates the pressure jump from the jet of the rocket launch engine in the ship’s air ducts 13 and 14 (see Fig. 2).

The drain valve consists of a plate 17 connected to a piston 18 provided with a shear element “a”. When the squib 19 is activated by pressure, the shear element is destroyed and the piston, moving downward, opens the drain valve.

Claims (5)

1. Missile launcher containing a block of at least two launch tubes with internal supporting longitudinal beams, characterized in that the pipe block is provided with an external irrigation system pipe, and each launch pipe is equipped with internal irrigation and chemical extinguishing pipelines, as well as system shutters thermostatic control, with a drain valve located at the rear of each launch tube. 2. The rocket launcher according to claim 1, characterized in that the pipeline of the external irrigation system is provided along the entire length with rows of three holes symmetrically located on each side of the pipeline through each row of holes. 3. The rocket launcher according to claim 1, characterized in that the pipelines of internal irrigation and chemical extinguishing are installed on the outside of the housing of the launch tube and are connected to the internal cavity of the launch tube by jet and conical type nozzles, respectively. 4. The rocket launcher according to claim 1, characterized in that the shutters are made in the form of two coaxial cylinders equipped with transverse cutouts that coincide with each other during operation of the thermostatic system and overlap before launching the rocket. 5. The rocket launcher according to claim 1, characterized in that the drain channel contains an actuator made in the form of a piston with a shear element.

Images