RU2286475C2 - Solid-propellant rocket engine - Google Patents

Abstract

FIELD: rocketry; solid-propellant engines.

SUBSTANCE: invention can be used at designing, developing and manufacturing of solid-propellant rocket engines. Proposed rocket engine contains body with fitted-in insert channel unrestricted burning charge and igniter arranged from side of charge front end face. Thin-walled diaphragm made of combustible material is installed behind rear end face of charge. Through cuts are made over periphery of diaphragm.

EFFECT: improved reliability of ignition of solid-propellant charge, and weight-and-dimension and performance characteristics of solid-propellant rocket engine.

2 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 propellant rocket engines (solid propellant rocket engines).

One of the urgent tasks of the design and development of solid propellant rocket engines is to create favorable conditions for reliable ignition (ignition) of solid rocket fuel (TRT) charges and to ensure a stable output of solid propellant rocket engines in operating mode. The fulfillment of this task is especially important under the condition of high heat losses in the initial period of engine operation, for example, in designs of short-time solid propellant motors that are usually not equipped with special thermal protection for the housing.

The solution of such problems to one degree or another is reflected in the patents: RU 2053401, RU 2170842, RU 2185522, RU 2212557, RU 2211356, US 3564845, US 4503773, RU 2170842. In the closest to the patented design (Figure 1) according to US Pat. RU 2053401 dated January 27, 1996 (prototype) is partially implemented (due to the closure of the charge channel from the front cover of the solid propellant rocket motor) an approach aimed at maximizing the use of thermal energy of the igniter for its intended purpose - to ignite the charge of the TRT and minimize unnecessary energy dissipation. However, despite the certain effectiveness of the indicated technical solution, it has a significant drawback, namely: the efficiency of the prototype design due to the partial localization of the combustion products (ps) of the igniter, as a rule, of gunpowder (including k-phase) in a limited volume near the front cover of the engine worsens the conditions of ignition of the surfaces (outer channel) of the TRT charge. The specified disadvantage of the design of the prototype is especially significant in solid propellant rocket engines of large elongation. In this case, partially purified from the k-phase smoke powder when moving along the gap “charge-housing solid propellant rocket motors” intensively lose temperature and are practically not able to ignite the charge TRT.

An object of the invention is the creation of the design of solid propellant rocket motors with high reliability of ignition of the charge (launch solid propellant rocket motors), with improved weight and size and operational characteristics.

The essence of the patented technical solution is illustrated in figure 1, 2, 3, 4.

Figure 1. Prototype design:

1 - housing with nozzle block;

2 - charge;

3 - igniter;

4 - membrane.

Figure 2. The nature of the distribution of the products of combustion of the igniter in the design of the prototype:

1 - housing with nozzle block;

2 - charge;

3 - igniter;

4 - membrane;

5 - k-phase ps

Figure 3. Patented design of solid propellant rocket motors:

1 - housing with nozzle block;

2 - charge;

3 - igniter;

4 - membrane.

Figure 4 The nature of the distribution of the products of combustion of the igniter in the patented design:

1 - housing with nozzle block;

2 - charge;

3 - igniter;

4 - membrane;

5 - k-phase ps

The technical result of the invention consists in the execution of a solid fuel rocket engine (Figure 3), comprising a housing with a nozzle block 1 with an all-round insertion channel charge 2 placed therein and an igniter 3 located on the front of the front end of the charge, while the engine is equipped with a thin-walled membrane 4 installed directly behind the rear end of the charge, overlapping the channel and, in whole or in part, the gap between the engine housing and the outer surface of the charge.

In this case, the membrane is made of combustible material, for example polyethylene, in the form of a disk, on the periphery of which there are through slots.

The invention consists in the inhibition of the flow ps igniter both in the gap and in the channel, at the rear end of the TRT charge. This allows you to increase the stay time igniter over flammable surfaces (outer surface, surface of the charge channel) and drop on the surface of the charge a substantial part of the k-phase (incandescent “burning particles.” “Burning particles” - in relation to smoke powder, mainly used to ignite charges from ballistic solid rocket fuels , - potassium sulfides, carbon particles, unburned particles of the smoky powder itself) and thereby ensure effective ignition of the charge.

In the absence of a membrane behind the rear end of the charge, the main part of the k-phase “flies” over the TPT charge surfaces, without contacting them, into the pre-nozzle volume and then through the nozzle block of the solid propellant. The implementation of the peripheral slots at the membrane allows you to adjust the level of the maximum peak pressure in the engine at the time of ignition, practically without reducing the efficiency of the landing K-phase PS igniter.

The implemented technical solution allows more efficient use of a sample of igniter for its intended purpose - to ignite the charge and reduce the useless dissipation of thermal energy of the igniter. This, in turn, allows to improve the weight and size characteristics of solid propellant rocket motors by reducing the mass of the igniter. In addition, it helps to reduce the smoke pop of solid propellant rocket engines in the initial period (by reducing the emission of the k-phase of the igniter), which significantly increases the reliability of guidance of guided missiles at the target.

Salient features of the patented invention are the installation of a thin-walled combustible membrane behind the rear end of the TPT charge and the execution of through slots on the membrane periphery.

The performance of the patented design was tested in the solid propellant rocket engine with the following parameters:

- housing steel, diameter 125 mm

- comprehensive combustion charge from ballistic TPT:

- length 150 mm - outside diameter 116 mm - channel diameter 50 mm - igniter 1.5 g of smoke powder DRP-2   film bag

- membrane polyethylene disk with a thickness of 1.0 ... 1.2 mm

- through slots on the periphery of the membrane:

- length 5 ... 6 mm - slot width 1 mm - number of slots 6

The solid propellant rocket motor includes a housing with a nozzle block 1, a channel charge TRT of all-round combustion 2 placed therein, and an igniter 3 mounted on the front of the front end of the charge, and a membrane 4 on the side of the rear end of the charge.

The solid propellant rocket motor works as follows: the igniter hitch is ignited by the initiator, ps which, moving along the outer surface and the surface of the charge channel, ignite them. Moreover, the flow ps the igniter is inhibited by a combustible membrane installed at the rear end of the charge, which increases the deposition of the k-phase on the surfaces of the charge and contributes to a more efficient ignition of the latter and a reliable conclusion of the solid propellant rocket to the operating mode.

A positive result of the invention is to increase the efficiency of solid propellant rocket motors.

Claims (2)

1. A rocket engine of solid fuel, comprising a housing with an all-round insertion channel charge placed inside it, an igniter located on the front of the front end of the charge, characterized in that a thin-walled membrane of combustible material is installed behind the rear end of the charge, along the periphery of which there are through slots. 2. Rocket engine of solid fuel, characterized in that the membrane is made of polyethylene.

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