RU2329391C1 - Solid-propellant charge igniter - Google Patents

Abstract

FIELD: blasting.

SUBSTANCE: solid-propellant charge igniter comprises a weighted portion of an igniting mixture placed into a plastic film body and localised therein. The body is formed of separate casings with flanges attached to the top or to the bottom of the body. A part or all of the peripheral casings are not filled with said weighted igniting mixture, while the casings and the top of the igniter body are made of carbon-black reinforced high-pressure polyethylene, disoriented in the longitudinal and transverse directions.

EFFECT: improving operational reliability of the igniter and ease of its manufacture.

3 cl, 7 dwg

Description

The invention relates to the field of rocket technology and can be used in the design, development and manufacture of igniters for solid rocket fuel (TRT) charges of rocket engines (RD), gas generators (GT), powder pressure accumulators, and other devices.

Known designs of igniters for charges TRT (Figure 1), the shells of which are made of film materials, including in the form of several shells filled with an ignition hinge (HV) and fastened together by a common cover for flanging the shells (US Pat. RU 2212557 from 09.09. 2003). The specified design is accepted by the authors as a prototype.

Advantages of the prototype design:

- ease of manufacture, low cost;

- high manufacturability in manufacturing;

- increase the weight perfection of the taxiway (GT);

- high reliability in operation.

However, the design of the prototype has a significant drawback.

Due to the small thicknesses of the films, usually 100 ... 500 microns, used for the shells of the igniter body, the possibility of grinding of the latter during mechanical-climatic, including vibration-shock loads during the operation of the taxiway (GG) and rockets is not ruled out.

In this case, not only the igniter tightness can be violated. Partial or complete emptying of the igniter body is possible (VN spilling into the free volume of the taxiway), which will inevitably lead to a refusal to start the taxiway.

An object of the invention is to increase the reliability of the igniter in the composition of the taxiway (GG).

The technical result of the invention consists in the implementation of the igniter charge of solid rocket fuel in the form of a sample of igniter composition, placed in the housing of the polymer film and localized in it. In this case, the igniter body is made of separate shells with flanges fastened to the cover and the bottom of the body. Part or all of the peripheral membranes are not filled with an igniter (VN). Depending on the design of the igniter fixing unit, as applied to a particular missile system, the blank (buffer) shells may be shells either from the side of the lid or bottom of the igniter, or from its side surface.

At the same time, a black-filled high-pressure polyethylene disoriented in the longitudinal and transverse directions is used as a film polymer material for the shells of the igniter body and cover, and the shells are made in the form of coaxial glasses.

The specified technical result of the invention allows to provide increased operational reliability of the igniter.

The invention consists in eliminating damage (rubbing) of the walls, bottom, cover of those shells that are filled with HV, due to the introduction of peripheral (buffer) unfilled HV shells into the igniter design (Figure 2-7), the mechanical damage of which does not affect the performance igniter. In case of damage to the outer walls of the peripheral shells, in any case, VN is localized at its location in the internal cavities of the igniter, and its reliable ignition from the directional force of the initiator (squib).

The execution of all the igniter shells from disoriented polyethylene (PE) allows for uniform shrinkage of the molded igniter body in the longitudinal and transverse directions, and the blackened filling of PE makes it possible to increase the safety of the patented manufacturing method in terms of reducing (eliminating) the accumulation of static electric charge on the igniter body during manufacturing and operation.

The patented invention is illustrated by graphic materials.

Figure 1. Prototype igniter design:

1 - cover

2 - hitch igniter composition,

3 - walls of the shells of the igniter body,

4 - flanging.

Figure 2. Patented igniter design

1 - cover

2 - linkages auxiliary composition,

3 - walls of the shells of the igniter body,

4 - flanging,

5 - buffer cavity.

Figure 3, 4, 5, 6, 7 - Design options patentable design of the igniter.

The patented design of the igniter (Figure 2) includes: the cover of the igniter body (1), the hinge of the igniter composition (2), the walls of the shells of the igniter body (3), the flanging (4), the buffer cavity (5). Based on the specific features of the placement of the igniter in the composition of the taxiway, buffer cavities can be present both from the bottom and the cover of the igniter, and from the side of the side surface, in various combinations that are appropriate from the point of view of ensuring the operational reliability of the ignitor (Figure 3-7).

The igniter operates as follows.

When the initiator is triggered, the igniter is ignited in one of the igniter cavities. The high-temperature products of combustion generated during the combustion of the high-temperature ignition provide ignition of the high-voltage in all ignitor cavities and subsequent ignition of the charge of solid rocket fuel.

Claims (3)

1. The igniter of the charge of solid rocket fuel, made in the form of a sample of the igniter composition, located in the housing of the polymer film and localized in it, while the housing is made of separate shells with flanges fastened to the cover or bottom of the housing, characterized in that part or all the peripheral shells are not filled with an igniter, and the shells of the igniter body and the cover are made of fenced-in polyethylene. 2. The solid rocket fuel charge igniter according to claim 1, characterized in that the igniter shell shell and cover are made of high pressure polyethylene disoriented in the longitudinal and transverse directions. 3. The igniter charge of solid rocket fuel according to claim 1, characterized in that the shell of the igniter body is made in the form of coaxial glasses.

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