RU2458244C1 - Solid-liquid propellant rocket engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises housing with bottom and channel charge secured to housing. Said charge is provided with radial slots and transverse annular slot formed by thin-wall permanent element to fit radial slots. Said thin-wall permanent element mirrors the housing front bottom shape from the joint of said element with front bottom to charge channel.

EFFECT: increased filling of engine chamber with fuel, simplified production.

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Description

The invention relates to rocket technology and can be used in the design of the march stages of rocket engines for solid fuel (RTTT).

In the constructions of strongly bonded cylindrical channel charges with elliptical bottoms of modern marching solid propellant rocket engines, an inclined annular transverse gap is used as a compensator for the initial combustion surface (Rocket and space technology, No. 35, 1980, p.12).

The use of such designs of charges allows you to implement the current diagram of the second flow rate with small deviations (8-10%) of the maximum value from the average. However, the class of charges under consideration has certain drawbacks associated primarily with a high level of stress-strain state (SSS) at the apex of the annular gap that occurs when the curb case is cooled due to temperature shrinkage and elastic movements of the body and bottom under pressure loading.

Known adopted for the prototype solid propellant rocket engine according to the patent of the Russian Federation No. 2154183 (publ. 08/10/2000), containing a housing with bottoms, bonded to the housing channel charge, equipped with an annular gap.

The separation of the charge into two parts using the provided design of the cuff with the tips, the location of the surfaces forming the burning surface of the annular gap, at an acute angle to each other, eliminated the fuel jumper between the apex of the annular gap and the engine housing, thereby solving the strength issues related to the design’s operability charge and slightly reduce the width of the gap across the entire diameter.

However, the known technical solution has several disadvantages associated with technological difficulties in the manufacturing process. In particular, the use of a traditional manufacturing scheme using technological equipment for forming an annular gap is difficult due to the need to extract technological equipment, the height of which exceeds the diameter of the channel. In addition, the design of the snap-in, forming the annular gap of the prototype, is complicated due to the large number of elements that require connection between each other when assembling the snap-in in the housing and subsequent extraction after charge manufacture. This is also a significant obstacle in order to minimize the acceptable for this design from the point of view of strength and gas dynamics disclosure of the compensator of the initial combustion surface in the form of an annular gap, which affects the increase in volumetric filling of the housing with fuel and, accordingly, the efficiency of the engine.

The task of the invention is to develop a solid-propellant rocket engine design that can increase its efficiency by increasing the engine chamber fill factor with fuel by creating conditions to minimize the allowable from the point of view of guaranteed disclosure of the compensator of the initial combustion surface and its complete ignition while simplifying the manufacturing technology and subsequent extrusion charge and maintaining the pattern of charge burn and changes in current character ISTIC time.

The problem is solved by the claimed design of a solid propellant rocket engine containing a housing with bottoms, a channel charge bonded to the housing, provided with an annular gap. The peculiarity lies in the fact that the charge is additionally equipped with radial slots adjacent to one of the burning surfaces to the annular gap, made transverse and formed by a thin-walled non-removable element, in mirror image reproducing in shape the front bottom of the case from the point of fastening the specified element with the front bottom to the charge channel.

The analysis of the prior art shows that the inventive solid propellant rocket engine differs from the prototype in the presence of radial slots adjacent to the burning surface of the annular gap and improve its flammability; another form of burning surface; the creation of the combined combustion surfaces of the radial slots and the annular gap; minimized opening formed by two types of cracks of the compensator of the initial combustion surface.

In the prior art there is no solid propellant rocket engine in which the proposed combination of essential features would take place, but it was this combination that determined the solution of the problem.

Radial slots additionally connect the burning surface of the annular gap with the charge channel, thereby contributing to an increase in the cross section through which the combustion products of the fuel from the narrow annular gap enter the channel, which leads to a decrease in the gas-dynamic charge intensity.

When forming an annular gap using a thin-walled non-removable element, the tool feathers for radial slots are adjacent to it and are a sufficiently reliable supporting support, which provides the required location of the element in the housing. The feathers of the snap can also be used as an element for attaching a thin-walled, non-removable element in internal diameter.

The essence of the proposed design of a solid propellant rocket engine is illustrated by a graphic image, which shows part of a longitudinal section of the engine.

The engine comprises a housing 1 with bottoms 2 (the rear bottom is not shown), a charge 3 bonded to the housing, having a central channel 4, a thin-walled non-removable element 5, forming a through annular gap, and radial slots 6.

After the manufacture and polymerization of the charge 3, the subsequent removal of the needle through the channel 4 remove the snap elements forming radial slots 6.

The proposed design of a solid propellant rocket engine operates as follows. After the operation of the igniter (not shown), the channel 4 and the thin-walled non-removable element 5, and then the through annular gap formed by it, are ignited. The combustion process occurs in parallel layers. It should be noted that the burning rate of a thin-walled non-removable element and, accordingly, its material (for example, fluoroplastic, aluminum) are determined when designing a particular engine based on the fact that the burning speed of the specified element should be greater than or equal to the burning speed of the charge.

The proposed technical solution is practicable. The creation of such structures is relevant and promising in view of the increased efficiency of missile systems.

Claims (1)

A solid propellant rocket engine comprising a housing with bottoms, a channel charge bonded to the housing, provided with an annular gap, characterized in that the charge is additionally equipped with radial slots adjacent to one of the burning surfaces to the annular gap, made transverse and formed by a thin-walled, non-removable element, reproducing in mirror image in shape, the front bottom of the housing from the point of attachment of the specified element with the front bottom to the charge channel.

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