RU2542709C1 - Solid-propellant rocket engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises housing with the main slotted-channel charge with partial armouring and extra solid-propellant charge aligned therewith. Armouring is applied on the main charge channel cylindrical part. Said extra charge feature star-like shape of inner channel and is glued in the main charge conical part via mid ply of elastic heat-resistant material.

EFFECT: higher factor of engine housing filling, simplified configuration.

3 cl, 2 dwg

Description

The invention relates to rocket technology, and in particular to the design of large-sized rocket engines (solid propellant rocket engines) with a mixed solid fuel (CTT) charge bonded to the body.

One of the main indicators of the quality of the fuel charge design for solid propellant rocket engines is the fill factor of the housing with fuel. However, an increase in the volumetric filling of the housing with fuel should be linked to the need to have a developed initial combustion surface and a rectangular pressure-time diagram. The design must withstand all the envisaged operational loads and ensure the extraction of the forming equipment after the manufacture of the charge. To increase the fill factor of the solid propellant rocket hull, various combinations of primary and secondary charges are used.

In the prior art, solid propellant rocket motors (US patent No. 2 755520, NKI 60-35.6), adopted for the prototype, comprising a housing, a main cylindrical charge with partial armor fastened with it, in the channel of which an additional charge of solid fuel is coaxial with the main channel, is known.

The disadvantages of the described technical solution include the complexity of the additional charge placement scheme, for the fastening of which the use of additional structural elements is required, which leads to an increase in the passive weight of the engine and a decrease in the fill factor of the engine housing.

The present invention is to simplify the layout of the additional charge and increase the fill factor of the motor housing.

The problem is solved by the proposed design of the solid propellant solid propellant rocket engine, including a housing, a main channel-slotted charge fastened with it with partial armor, in the channel of which an additional charge of solid fuel is coaxial with the main one, while the main charge is applied to the cylindrical part of the channel, and the additional one has a star shape internal channel and glued to the conical part of the main charge channel through an intermediate layer of elastic heat-resistant material.

In particular, on the outer surface of the additional charge there are longitudinal ribs along which it is glued to the main charge.

In particular, the additional charge is made of several separate blocks.

The proposed scheme for placing an additional charge is simpler, since it is not necessary to use additional fasteners (bearing bases) to increase the passive weight of the engine to place the charge glued into the channel.

The star-shaped form of the additional charge provides the maximum surface and minimum burning time of the additional charge.

The presence of an elastic layer reduces the separation forces caused by the deformation of the main charge under the influence of pressure or temperature.

The presence of fins on the outer surface of the additional charge allows to reduce the burning time of the glued charge and allows to increase the flow area for the movement of combustion products and the initial surface of the charge.

The manufacture of charges in the form of separate blocks facilitates their gluing into the main charge and reduces the level of stress-strain state of the main charge associated with the placement of an additional charge in its channel.

The proposed design is illustrated by drawings, figure 1, 2. Figure 1 shows a General view and a cross section of the main and additional charges, figure 2 shows an additional view of the charge in the form of separate blocks.

The main charge 2 is placed in the housing 1, an additional charge 5 is pasted into the channel 3 of the main charge 2 through an elastic layer 4, the cylindrical part of the channel 3 of the main charge 2 has a reservation 6.

The proposed solid propellant rocket motor works as follows.

After the igniter is activated, the cracks light up, the nozzle part of the surface of the main charge 2 and an additional charge 5.

The cylindrical part of the main charge channel 2 is under reservation 6 and is not lit. Within 3-4 seconds, an additional charge burns and the entire surface of the main charge is connected to combustion. Subsequently, the charge operates in the usual way.

To determine the area of reservation of the surface of the main charge, it is necessary to compare the gas intake from the additional charge and the free surface of the main charge.

Examples of specific performance.

Example 1

Large-sized solid propellant solid-propellant solid-state solid-propellant solid-propellant solid-propellant solid-propellant charge, the scheme of which is shown in Fig. 1, an additional star-shaped charge is glued into the conical section. Sizes of the conical section: diameters 400 and 800 mm, length 1000 mm. The surface of the additional charge is 200 dm ² . The burning rate of the main charge is 10 mm / s, and an additional 18 mm / s. Thus, in order to maintain the gas intake corresponding to the main charge, in the latter it is necessary to reserve 360 dm ^{2 of the} surface. The length of the cylindrical channel of the main charge is 3000 mm. To compensate for the gas intake from an additional charge, it is necessary to reserve a cylindrical channel for a length of 2800 mm for 3 s. The reservation can be made by gluing the main charge used in the protective-fixing layer of the nylon technical fabric with a repeated coating with glue onto the channel. The mass of the additional charge is 415 kg or 2.5% of the mass of the main charge. An intermediate layer with a thickness of 10 mm is made, for example, of heat-resistant microporous rubber grade 5116, from which a protective-fixing layer of the main charge is made. This rubber is heat resistant and is not subject to diffusion of fuel components. Gluing an additional charge is also made by glue which is used in ZKS.

Example 2

The additional charge shown in FIG. 1 has six ribs along which it is glued into the main charge channel. The number of ribs, their sizes are determined by the characteristics of a particular charge. In this example, the additional charge channel is a six-pointed star, therefore, the number of edges is also equal to six. The height of the ribs at the entrance is 40 mm, the length of the ribs along the arc is 150 mm. The size of the channels between the ribs increases towards the rear bottom. The presence of these ribs allows you to increase the flow area for the expiration of combustion products by 40%, increase the initial combustion surface by 35% and reduce the burning time of the additional charge by 30-35%.

Example 3

The additional charge (Figure 2), as in example 1, has a star-shaped configuration of the internal channel, but is made of five separate blocks. A layer of elastic rubber 5116 with a thickness of 10 mm is applied to each block using the glue used in the ZKS; through the elastic layer, each block is glued to the main charge channel. The proposed design of the charge allows to increase the fill factor of the housing with fuel by 2.5%.

The proposed solution is promising and relevant, as it allows simple means to increase the effectiveness of missile systems. Currently, tests of the proposed arrangement of the additional charge at the pilot plant are being tested.

Claims (3)

1. A rocket engine of solid fuel, comprising a housing, bonded with it the main channel-slotted charge with partial reservation, in the channel of which coaxial to the main placed an additional charge of solid fuel, characterized in that the reservation on the main charge is applied to the cylindrical part of the channel, and an additional charge has a star-shaped shape of the inner channel and is glued to the conical part of the channel of the main charge through an intermediate layer of elastic heat-resistant material. 2. The solid propellant rocket motor according to claim 1, characterized in that on the outer surface of the additional charge there are longitudinal ribs along which it is glued into the main charge. 3. The solid propellant rocket motor according to claim 1, characterized in that the additional charge is made of separate blocks.

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