RU2408833C1 - Ignition method of powder charge onboard moving missile train and device for its realisation - Google Patents

Abstract

FIELD: blasting operations.

SUBSTANCE: ignition method of powder charge onboard the moving missile train involves activation of ignition device. Ignition device is activated by its interaction with striker located at the missile track. Ignition device implementing the above method includes initiation means, housing with blasting chamber inside which an igniter is located. Initiation means are made in the form of elongated charge of explosive agent, one end of which is arranged in blasting chamber, and the other one is located outside the housing and enclosed in the casing fixed on the housing. A nozzle is made in the housing. Return valve is installed between nozzle and blasting chamber so that combustion products of the igniter can flow from the device housing through the nozzle. Elongated charge of explosive agent of the initiation device can be made in the form of detonating cord. On the part of detonating chord, which is located outside the housing, there can be arranged the charge of plastic explosive.

EFFECT: improving starting reliability of rocket engines and pyrotechnic devices.

4 cl, 6 dwg

Description

The invention relates to a testing technique. The preferred area of application is high-speed rocket track testing.

A known method of starting a rocket engine using an igniter assembly (US patent No. 3750581, IPC F42B 15/00; F02K 9/08, publ. 07.08.1973). The rocket engine igniter assembly has an igniter capsule (ignition device), which is installed at the base of the liner. From the igniter capsule, the flame is transferred to an igniter charge (powder charge) located inside the rocket engine, using an igniter cord, one end of which is in the sleeve, and the other passes to the igniter charge. Further, the products of combustion of the igniter charge ignite the solid propellant charge of the rocket engine. The disadvantages of this method are the long burning time of the igniter cord and its instability. In addition, a separate device is required to initiate the igniter capsule, which complicates this method of starting a rocket engine.

A known method of starting the linear steps of a moving rocket train described in the article D.J. Rigali and L.V. Felt2. High speed Monorail Rocket Sleds for Aerodynamic Testing at High Reynolds Numbers, "Journal of Spacecraft and Rockets", v.5, No. 11, p.1341-1346, 1968 (D.J. Rigely and L.V. Felti. High-speed monorail rocket carts for aerodynamic testing at high Reynolds numbers Translation No. 82087/0 VINITI, M., 1970, p.11), selected as a prototype for the proposed method. Missile train - a set of missile carts (stages of a missile train), each of which includes one or more solid propellant rocket engines interconnected and equipped with devices (such as slide supports) for translational movement along the rail guide of the missile track. The linear steps of a rocket train are usually called all its steps except for the starting one - the first in the order of launch. The method consists in using an on-board ignition system, by means of which an ignition means is initiated by an electric pulse. From a means of ignition, a powder charge is ignited, igniting the solid fuel of a rocket engine. The on-board ignition system consists of two separate starting devices. Each starter includes an accelerometer that integrates an accelerometer and a power source. The starting device is adjusted so that the engines start at a given level of overload. The disadvantages of this method are the complexity and high cost of the ignition system, which also worsens the energy-mass characteristics of the rocket train.

A known gas-dynamic pressure source (RF patent No. 2139927, IPC ⁶ F41F 1/00, publ. 08/27/99, bull. No. 24), comprising a housing in which a hollow cylindrical powder charge with a rod axial igniter and an ignition means (detonator) is placed. The igniter of the powder charge is made of explosive (in particular, in the form of a detonating cord) and is installed with a gap in the cavity of the powder charge. The disadvantage of this device should be attributed to the fact that the ignition means is located in the housing of the pressure source, which necessitates the supply of an initiating pulse (electric current, shock, pricking, etc.) directly to the housing of the pressure source. This means that in order to ignite a powder charge on board a moving rocket train, it is necessary to have on it the same source of the initiating pulse (battery, trigger mechanism, etc.). As a result, the energy and mass characteristics of the train deteriorate and problems arise in determining the optimal moment of transmission of the initiating pulse from its source to the ignition means.

A device for igniting powder charges of pyrotechnic installations (RF patent No. 2105263, IPC ⁶ F42B 3/10, publ. 02.20.1998), selected as a prototype. The device comprises a housing with an explosive chamber, a node for introducing a charge into the chamber, an electric current source, and means for initiating fire. A bulk powder charge and an igniter are placed in the chamber, the grains of which are coated with a thin layer of conductive material. Fire initiation means is located in the lower part of the blast chamber and is made in the form of a dielectric insert with a conical recess in the center for the igniter and two electrodes for the formation of an electric arc. The disadvantages of the prototype are the same as that of the analogue.

The technical problem to be solved is the creation of a method and a device realizing it for igniting a powder charge on board a moving rocket train.

The expected technical result when using the proposed method and device is to increase reliability and reduce the cost of starting rocket engines and pyromechanical devices located on board a moving rocket train.

The technical result is achieved through the application of the method of ignition of the powder charge on board a moving rocket train, including the initiation of the device for ignition. In contrast to the prototype in the inventive method, the initiation of the device for ignition is produced by its interaction with the drummer located at the rocket track.

The initiation of a device for ignition by interacting with a striker makes it possible to reliably ignite a powder charge on board a moving rocket train without using an electronic automatic ignition system.

The location of the striker at the rocket track provides the launch of the rocket engine (s) of the linear stage of the moving rocket train or pyromechanical device, placed on board the moving rocket train, at a given point.

The technical result is also achieved through the use of a device for igniting a powder charge containing initiation means and a housing with an explosive chamber, inside of which an igniter is located. Unlike the prototype in the inventive device, the initiating means is made in the form of an elongated explosive charge, one end of which is placed in the explosive chamber, and the other is located outside the housing and enclosed in a casing mounted on the housing. A nozzle is made in the housing. Between the nozzle and the blast chamber, a check valve is located with the possibility of the expiration of the igniter combustion products through the nozzle from the device body.

An elongated explosive charge of the initiating means may be in the form of a detonating cord.

A plastic explosive charge may be placed on the part of the detonating cord located outside the housing.

The implementation of the initiation means in the form of an elongated explosive charge provides the possibility of detonation initiation by the shock method (the explosive ability to initiate from the impact is highlighted, for example, in the source of the Explosion Physics, edited by KP Staniukovich. - M .: Nauka, 1975, p. .181-194) and transferring it to the igniter, that is, it allows initiating the ignition device by interacting with the hammer.

Placing one end of the explosive charge in the explosive chamber allows the initiating pulse to be transmitted to the igniter located therein from the detonating explosive charge.

The location of the second end of the explosive charge outside the housing allows the interaction of the device for ignition with a striker to avoid destruction of the device.

The conclusion of the end of the charge located outside the casing in the casing, mounted on the casing, provides its resistance to mechanical and thermal influences from the incoming air flow during high-speed movement of the rocket train to interact with the striker.

The execution in the nozzle body ensures the expiration of the products of combustion of the igniter from the device into the cavity where the combustible powder charge is located.

The location of the non-return valve between the explosive chamber and the nozzle with the possibility of the outflow of igniter products from the device through the nozzle prevents the outflow of combustion products from the cavity where the powder charge is located (in a rocket engine or in a gas-dynamic pressure source) into the atmosphere through the opening for introducing the means initiation in the enclosure.

Performing an elongated explosive charge of the initiating means in the form of a detonating cord makes the equipment of the device more technological.

Placing on the outside of the body part of the detonating cord of a charge of a plastic explosive allows you to vary the sensitivity of the initiating means using various types of plastic explosive depending on the speed of interaction of the device for ignition with a projectile.

The inventive method of ignition of powder charges on board a moving rocket train and a device for its implementation are illustrated by the drawings: figure 1 - device for igniting a powder charge; figure 2 - a device for igniting a powder charge with an elongated explosive charge of the means of initiation, made in the form of a detonating cord with a charge of plastic explosive; figure 3 is a diagram of the relative position of the striker and the device for igniting a powder charge intended for ignition of solid fuel of a rocket engine of a linear stage of a moving rocket train; figure 4 is an external view of a device for igniting a powder charge mounted on a solid propellant rocket engine of a linear stage of a rocket train; 5 is a diagram of the relative position of the striker and the device for igniting a powder charge placed in a gas-dynamic pressure source of a pyromechanical device located on board a moving rocket train; 6 is a diagram of the operation of the check valve after ignition of the powder charge on board a moving rocket train.

A device for igniting a powder charge (Fig. 1) consists of a housing 1 (the housing in this embodiment is made up of two components) with an explosive chamber 2, inside of which an igniter 3 is placed, which can be made, for example, in the form of a powder charge (in this the igniter 3 is fixed in the explosive chamber 2 by a diaphragm 27 made of a material destroyed, for example, foam). The initiation tool is made in the form of an elongated explosive charge 4, one end 5 of which is placed in the explosive chamber 2, and the other end 6 is located outside the housing 1 and is enclosed in a casing 7 mounted on the housing 1. In the housing 1 there is a nozzle 8. Between the nozzle 8 and an explosive chamber 2 has a non-return valve 9 with the possibility of the expiration of the products of combustion of the igniter 3 through the nozzle 8 from the housing 1 of the device. In this embodiment, the check valve 9 consists of a locking element 10 located in the channel 11 of the housing 1 with the possibility of movement between the shoulder 12 and the nozzle 8. In the locking element 10 there are holes 13 communicating with the nozzle 8 and the cavity of the explosive chamber 2 when the locking element 10 is pressed to the end of the nozzle 8.

An elongated explosive charge 4 of the initiation means can be made in the form of a detonating cord (figure 2).

On the outside of the housing part of the detonating cord 4 can be placed a charge of plastic explosive 14 (figure 2).

The method of ignition of the powder charge 15 on board a moving rocket train is illustrated in figure 3, 5.

The linear stage of the rocket train 16 (Fig.3, 5) moves along the rail guide 17 of the rocket track. On board the linear stage 16, a device 18 is fixed for igniting the powder charge 15.

The powder charge 15 can be designed, for example, for igniting solid fuel 19 of a rocket engine 20 of a linear stage of a rocket train 16 (Figs. 3, 4).

Also, the powder charge 15 can be placed in a gas-dynamic pressure source 21 of the pyromechanical device 22 on board the linear stage of the rocket train 16 (Fig. 5). The initiation of the ignition device 18 (FIGS. 3, 5) is performed by its interaction with a fixed drummer 23 located at the rocket track.

The functioning of the device 18 for igniting a powder charge on board a moving rocket train is as follows.

At the moment of collision of the casing 7, in the channel of which one end 6 of the elongated explosive charge 4 is placed, which is a means of initiation (Figs. 1-5), with the striker 23 located at the rocket track, the explosive charge 4 is pulsedly compressed, as a result of which detonation is excited . The detonation wave, moving along the explosive charge 4, reaches the explosive chamber 2. The products of the explosion of the other end 5 of the explosive charge 4, located in the explosive chamber 2, ignite the igniter 3, whose combustion products, passing through the system of openings 13 of the check valve 9, flow out of the housing 1 devices through the nozzle 8, forming a force of flame, into the cavity where the ignitable powder charge 15 is located.

As a result of the effect of force of the flame on the powder charge 15 (Fig.4, 5), located on board the rocket train, it ignites. The combustion products of the powder charge 15 provide ignition of solid fuel 19 of the rocket engine 20 of the linear stage of the moving rocket train 16 (figure 4).

In the case of the location of the powder charge 15 in the gas-dynamic pressure source 21, the combustion products flow out of it into the working cavity 24 of the pyromechanical device 22, doing work on it to eject the test object 25 (Fig. 5).

After ignition of the powder charge 15, its combustion products, acting on the end face of the locking element 10 (Fig.6) of the check valve 9, move it all the way to the shoulder 12, thus blocking the channel 11 of the housing 1 and preventing its outflow into the atmosphere through the opening 26 housing 1.

The proposed method and device for igniting a powder charge on board a moving rocket train will increase reliability and reduce the cost of starting rocket engines and pyromechanical devices located on it.

The proposed technical solutions were tested experimentally in reverse tests. Ignition of the powder charge is recorded by electrical (pressure sensor) and optical (video camera) recording means.

Claims (4)

1. A method of igniting a powder charge on board a moving rocket train, comprising initiating an ignition device, characterized in that the initiation of the ignition device is produced by its interaction with a projectile located at the rocket track. 2. A device for igniting a powder charge, containing initiating means, a housing with an explosive chamber, inside which there is an igniter, characterized in that the initiating means is made in the form of an elongated explosive charge, one end of which is placed in the explosive chamber, and the other is located outside the housing and enclosed in a casing, mounted on the casing, a nozzle is made in the casing, a check valve is installed between the nozzle and the blast chamber with the possibility of the flow of igniter products from whisker device through the nozzle. 3. A device for igniting a powder charge according to claim 2, characterized in that the elongated charge of the explosive means of initiation is made in the form of a detonating cord. 4. A device for igniting a powder charge according to claim 3, characterized in that a plastic explosive charge is placed on the part of the detonating cord located outside the housing.

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