RU2432484C1 - Solid-fuel charge igniter for rocket engine - Google Patents

Abstract

FIELD: engines and pumps. ^ SUBSTANCE: igniter consists of the thermoplastic film housing made of back-extended polyethylene with equal shrinkage in lateral and longitudinal directions in a form of bowl-shaped revolution body with flanging and ignition mixture hinge located in it, and a cover attached to the housing along flanging. The cover is made of metal and attached to the housing by glue on the basis of thermoplastic rubber and indene coumarone resin. Note that there are notches equally performed at the cover periphery. Notch depth, diameter by notch depth and cover diameter are defined by ratios protected by this invention. ^ EFFECT: invention allows increasing of solid-fuel charge igniter for rocket engine reliability. ^ 3 cl, 4 dwg

Description

The invention relates to the field of rocket technology and can be used in the design, development and manufacture of solid fuel igniters for rocket engines (solid propellant rocket engine - solid fuel rocket engine), gas generators (GG), on-board actuators (BIM) rockets, ejection devices (KU), emergency rescue systems (CAC) pilots, etc.

In modern solid propellant rocket engines, gas turbines and other rocket systems, igniters are widely used, a sample of which is placed in a housing made of a polymer film. The advantages of such igniters compared to igniters whose casings are made of metal - steel or aluminum (aluminum alloys) are practically obvious: film igniters are easy to manufacture, provide less passive weight of the engine, exclude the formation of solid residues during combustion, which contributes to a lower torch and smoke generation and satisfactory operation of solid propellant rocket engines, gas turbines, rocket launchers and other missile systems as a whole.

As is known, solid propellant rocket ignitors are subject to stringent requirements to ensure ignition of charges in a given very short period of time (0.001 ... 0.005 s), to exclude delays in ignition and refusal to ignite. This requires the development of constructive measures to increase the reliability of ignition of both the ignitor’s ignitor hitch and to improve the ignition scheme of solid propellant rocket charges.

Design igniters with housings made of film materials according to US Pat. RU 2170842, RU 2212557, RU 2247254, RU 2288371, RU 2282743, RU 2309282, RU 2329391, RU 2329392 provide mainly high reliability of ignition of solid fuel charges in the required period of time, improved weight and size characteristics, technological and economic indicators.

However, all of the above igniter designs have a common drawback - the lack of reliable fastening (fixing) of the igniter in the combustion chamber of a rocket engine, which is accompanied by inefficient use of the energy of the igniter when igniting the igniter. This is due to the process of deformation (crushing), the movement of the igniter inside the CS, i.e. the loss of energy of the igniter to ignite the actual sample of the igniter, which is a significant drawback of existing designs of film igniters.

The authors adopted the invention according to US Pat. RU 2212557 C1, application 2002 101764 dated 01/17/2002, IPC F02K 9/95.

An object of the invention is to develop a design of an igniter of a solid propellant charge of a rocket engine with increased efficiency, high-quality ignition of a sample of an igniter and solid propellant charge in general.

, гдеThe technical result of the invention is to develop the design of the igniter (Figure 1) of the solid propellant charge of a rocket engine. The igniter comprises a body in the form of a cup-shaped body of revolution with a flange, a hitch of igniter composition placed in the body and a cover fastened to the body by flanging. The igniter body is made of a thermoplastic film with uniform shrinkage in the longitudinal and transverse directions, and the cover is made of metal and bonded to the flange of the case with adhesive based on thermoplastic elastomer (TEP) and indencumarone resin (IKS), modified solvents based on ethyl acetate, butyl acetate and nefras. The diameter of the igniter cover (D _cr ) is made in accordance with the ratio:

where

D _cr - the diameter of the combustion chamber of a rocket engine;

h _mouth - the depth of the reference annular ledge in the combustion chamber of a rocket engine.

Evenly around the periphery of the lid (Figure 3), cuts are made with a depth of h _cut > h _mouth, and a diameter along the depth of cuts (D _cut ) satisfies the ratio:

,

,

where D _reb - the outer diameter of the flanging of the igniter body;

D _cut - diameter along the depth of the cuts.

At the same time, a carbon black filled film can be used as a film for the igniter body, and steel as a cover material.

The invention is illustrated in the figures.

Figure 1. Patented igniter design

1 - igniter housing

2 - hitch igniter composition

3 - flare igniter housing

4 - igniter cover

5 - glue based on TEP and IKS

6 - peripheral cutouts in the igniter cover

Figure 2. Placing a patented igniter design in a rocket engine setting

7 - combustion chamber of a rocket engine

8 - charge of solid rocket fuel

9 - annular ledge in the combustion chamber

10 - front cover of the rocket engine

11 - squib (PP)

Figure 3. View A of the solid propellant rocket motor with the front cover removed

12 - slotted peripheral holes (between the cutouts of the igniter cover and the annular ledge KS)

D _s - the outer diameter of the solid propellant charge

Figure 4. The nature of the flow of the PS pyrocartridge and igniter in the solid propellant rocket engine (after the operation of the PP).

The essence of the invention lies in the efficient use of the energy of the squib (PP) for ignition (Figure 1) of the igniter sample (2), the patented design of the igniter and the efficiency of the solid propellant rocket engine in general. In terms of high-quality ignition of the igniter hinge (2), the effect is achieved both due to the passage of the combustion products of the pyro cartridge (11) along the axis of the igniter, and due to the reflection of the PP jet from the metal cover (4) of the ignitor in radial directions, which ensures effective ignitability of the entire hitch by weight inside the igniter housing (1). The latter is achieved due to the rigid fixation of the igniter body on the metal cover. In terms of increasing the efficiency of solid propellant rocket engines in general, the effect is achieved by combining the functions of the solid rocket motor divider and the igniter cover (4), which reduces the passive weight of the rocket engine. This effect is also provided due to the reliable fastening of the flare housing (1) of the flare (3) with the metal cover (4) of the igniter with glue (5) based on TEP and ICS. As experiments have shown, an adhesive composition based on these components provides a shear stress level at the film-steel contact of 5 kG / cm ² or more in the temperature range of ± 50 ° C, which ensures guaranteed fixation of the igniter at the bonding point both during the service life, and in combat use. The implementation of the diameter of the igniter cover equal to D _KC + h _mouth and uniform execution along the periphery of the cover of the cut-outs with a depth (h _mouth ) more than the depth (h _mouth ) of the annular ledge allows to realize (FIG. 2, FIG. 3) slotted peripheral holes (12) for supplying PS the igniter in the CS and ignition of the charge (8), and ensuring the conditions

guarantees the operability of the structure as a whole.

The requirement D _expr> D _sel provides serviceability (continuity, the continuity) of the node bonding flanging igniter housing with the igniter metal lid, and the condition D _expr <D _CS provides the slit gap between the COP and the ignition cap for the passage to the surface PS igniter charge.

Patented design is implemented as an igniter with the following characteristics:

- igniter case material - black-filled polyethylene;

- igniter cover material - steel;

- adhesive material for flanging the igniter body with a cover - adhesive composition based on TEP and IKS, modified with solvents based on ethyl acetate, butyl acetate and nefras;

- igniter sample - 9 g of powder DRP-2;

- geometric dimensions - in accordance with Figure 1;

- the adhesion level of the blackened filled polyethylene to steel was 5.2 kgf / cm ² .

Patented design works as follows (Figure 2). When the force of the flame of the igniter is affected by the igniter body (1), the latter is burned and the igniter hitch (2) lights up along the axis of the force. Force pyrocartridge abuts against the metal cover of the igniter (4) and "spreads" in radial directions, setting fire to the bulk of the igniter sample (Figure 4). The joint products of combustion of the PP (11) and the igniter through the peripheral holes (6) of the cover enter the CS (7) of the rocket engine and ignite the charge (8) of solid rocket fuel.

The positive effect of the invention is to increase the reliability and efficiency of ignition of charges TRT in the composition of rocket engines.

The igniter provided during the fire bench test as part of the solid propellant rocket engine the ignition of the charge and its output to the operating mode for a time of 0.003 s (the charge of comprehensive combustion from ballistic solid rocket fuel weighing 3.1 kg).

Claims (3)

1. The igniter of a solid propellant charge for a rocket engine, comprising a housing of thermoplastic film with uniform shrinkage in the longitudinal and transverse directions in the form of a cup-shaped body of revolution with flanging and a hinge of igniter composition and a lid attached to the flanging housing, characterized in that the lid It is made of metal and fastened to the housing by adhesive and indenkumaronovoy thermoplastic resin, wherein the cover evenly around the periphery of cutouts _expr depth h, where h _{in p>} h _{lips, mouth} where h - the depth of the annular shoulder in the engine combustion chamber, and the diameter of the recesses the depth D satisfies _expr
D _ot <D _vyr <D _KС ,
where D _reb - the outer diameter of the flanging of the igniter body;
D _KC - the inner diameter of the combustion chamber of a rocket engine, while the diameter of the cover D _cr igniter is made in accordance with the ratio
D _cr = D _KC + h _yct 2. A solid fuel igniter for a rocket engine according to claim 1, characterized in that the igniter cover is made of steel. 3. The solid-fuel charge igniter for a rocket engine according to claim 1, characterized in that the igniter body is made of black-filled polyethylene.

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