RU2435061C1 - Solid-propellant rocket engine - Google Patents

Abstract

FIELD: engines and pumps. ^ SUBSTANCE: solid-propellant rocket engine includes housing adjacent to the fastening frame, receiver connected to housing, four nozzles, charge and igniter. Receiver is equipped with four nozzle flanges the axes of which are perpendicular to longitudinal axis of rocket engine and to each other. Nozzles of rocket engine are attached to nozzle flanges of receiver. Housing and receiver are spherical; at that, radius of receiver is smaller than that of housing. Charge is rigidly connected to housing and has central channel. Value of burning propellant web is higher than or equal to difference between inner radius of housing and inner radius of fastening frame. ^ EFFECT: invention allows reducing the weight and dimensions of rocket engine, and simplifying its manufacturing technology. ^ 3 cl, 2 dwg

Description

The invention relates to rocket technology and can be used to create a solid fuel rocket engine (solid propellant rocket engine) emergency rescue system (CAC) spacecraft.

Known solid propellant rocket engine, the nozzle block of which is made according to the “pulling” scheme and is formed by several nozzles deployed backwards installed in the receiver (section) [Fakhrutdinov I.Kh., Kotelnikov A.V. Design and Design of Solid Fuel Rocket Engines: A Textbook for Engineering Universities. - M.: Engineering, 1987, 328 p., Ill., Page 28, Fig. 1.15, diagram (m)]. The housing containing the charge is connected to the receiver. The housing and receiver are cylindrical. The cylindrical shape of these elements determines their large mass. The fill factor of the indicated solid propellant solid fuel charge is low, because having a large internal volume "empty" receiver does not contain fuel. The mass of the nodes for connecting nozzles with the receiver’s cylindrical shell has been increased due to the need for measures to reduce the stress concentration in these nodes and due to the inevitable technological thickening of some sections of these nodes. The manufacture of the receiver of the specified solid propellant rocket is complicated due to the need for articulation of the nozzles with the cylindrical shell of the receiver.

The closest in technical essence and the achieved positive effect to the invention is the central solid propellant rocket engine ДУ САС of the Soyuz-TM spacecraft [On the life and work of academician B. P. Zhukov. - Tula: Grif and K, 2008. - 304 p., Ill., Pages 79, 80]. The central solid-propellant solid propellant rocket motor (position 3 in the figure and in the text) of the SAS remote control contains a housing, a cylindrical receiver, in which the nozzle mounting flanges are made. The charge is made of several insert checkers of ballistic powder, i.e. it has a small value of the burning arch, providing a short operating time (which is necessary for the solid propellant emergency rescue system). The above design has the following disadvantages.

1. The large mass of the body, due to

a) its cylindrical shape;

b) the large thickness of the heat-shielding coating, which is caused by the absence of the heat-shielding functions of the input charge;

c) the presence of massive gratings (diaphragms) for fixing the external charge.

2. The large mass of the receiver, due to

a) its cylindrical shape;

b) its large diameter (almost equal to the diameter of the case);

c) the need to connect the nozzle flanges with the cylindrical wall of the receiver. The necessary measures to reduce the stress concentration at the joints are associated with an increase in the thickness of these sections of the structure.

3. The large mass of solid propellant rocket motors as a whole (which, in addition to points 1, 2, is explained by the low coefficient of filling of solid rocket rocket motor with charge fuel), due to the fact that

a) the large internal volume of the "empty" receiver does not contain fuel;

b) the plug-in multi-cup charge itself is characterized by a low duty cycle.

4. The reliability of the receiver is reduced due to the complex technology of its manufacture.

5. The accuracy of the mutual arrangement of nozzle flanges (nozzles) is reduced due to the low manufacturability of the receiver.

The technical task of the present invention is to reduce the mass of the structure and dimensions of the solid propellant rocket motor, simplifying the manufacturing technology and improving the quality of the solid rocket motor.

The essence of the invention lies in the fact that in a solid propellant rocket engine (solid propellant rocket engine) comprising a housing interfaced with a mounting frame, a receiver connected to the housing, the receiver having four nozzle flanges, the axes of which are perpendicular to the longitudinal axis of the solid propellant rocket engine and to each other, four nozzles attached to nozzle flanges, charge, igniter, casing and receiver are made spherical, and the radius of the receiver is less than the radius of the casing. The charge is firmly bonded to the body and has a central channel, and the magnitude of the burning vault of charge is greater than or equal to the difference between the inner radius of the housing and the inner radius of the mounting frame. On the central channel of the charge can be made protrusions. An additional charge may be installed in the receiver.

The technical result is achieved as follows. It is known from sopromat that for loading the shell with internal pressure (with an equal radius), the spherical shape of the case and receiver (compared to the cylindrical one) provides a twofold decrease in the wall thickness. A sphere has a maximum internal volume with a minimum surface (mass). The radius of the receiver is smaller than the radius of the casing, which leads to a decrease in its mass, both due to a decrease in dimensions and due to a decrease in wall thickness with a decrease in the radius of the sphere. The execution of the charge is firmly bonded to the body and the shape of the charge having a central channel provides thermal protection by the charge of the inner surface of the body. At the same time, minimization of the mass of the heat-protective coating of the housing is achieved. The ability to replace the plug-in checkers of the prototype charge with a solidly-charged charge is ensured by the selection of the fuel composition with the high (maximum possible) burning rate necessary for short operating time. At the selected burning rate, the value of the burning arch of a strongly bonded charge exceeds the burning code of plug-in checkers, but nevertheless it turns out to be lower in comparison with traditional strongly bonded charges (since the burning rate cannot be infinitely large). Those. the relative radius of the central channel of the charge is large enough, which leads to a relatively small (for a strongly bonded charge) coefficient of filling the housing with fuel charge. The value of the burning dome of the charge is greater than or equal to the difference between the inner radius of the housing and the inner radius of the mounting frame. This achieves the simplicity of the tool, forming a channel in the process of manufacturing a charge. At the same time, it is possible either to perform protrusions on the central charge channel, or to arrange an additional charge in the charge channel. The presence of protrusions or an additional charge provides an increase in the fill factor of the solid propellant charge as a whole, compensating for the relatively small fill factor of the housing (with a separate consideration of the housing isolated from the solid propellant motor with a charge having only a central channel). The implementation of the receiver in the form of a sphere leads to the fact that the axis drawn through any nozzle flange passes through the center of the sphere (i.e., coincides with the axis of the sphere). In this case, the joint section of the nozzle flange with the receiver shell is axisymmetric. The axisymmetric shape of the joint section of the nozzle flange with the receiver section (casing) ensures smoothness and uniformity (along the circumference of the nozzle flange) of the interface with minimization of stress concentration. This leads to minimizing the mass of the receiver with an increase in its reliability during the perception of mechanical loads (for example, in-chamber pressure). At the same time, the manufacturability of the receiver is being improved.

This technical solution is not known from the patent and technical literature.

The invention is illustrated by the following drawings:

figure 1, 2 shows a longitudinal section of the variants of solid propellant rocket motors.

The solid propellant rocket engine (RTTT) comprises a spherical housing 1 (see FIG. 1). The housing 1 is paired with a mounting frame 2. A receiver 3 is mounted on the housing 1, made in the form of a sphere with a radius smaller than the radius of the housing 1. The receiver 3 is mounted on the housing 1 by means of a response mounting frame 4, paired with the receiver 3. The receiver 3 is equipped with four nozzle flanges 5, the axes of which are perpendicular to the longitudinal axis of the solid propellant rocket motor and to each other. Four nozzles 6 are attached to the nozzle flanges 5. The charge 7 is firmly attached to the housing 1 and has a central channel 8. The magnitude of the burning dome of charge 8 is greater than or equal to the difference between the inner radius of the housing 1 and the inner radius of the mounting case frame 2. On the central channel 8 of charge 7 protrusions 9 can be made (see figure 2). In the receiver 3 can be installed an additional charge 10 (see figure 1, 2). In the embodiment shown in figure 2, the additional charge 10 may be absent, but may have a shortened length. The igniter 11 is installed, for example, on the housing 1 (inside the central channel 8 of the charge 7). The housing 1 and the receiver 3 may contain nodes 12 connecting the solid propellant rocket engine with adjacent rocket compartments.

The device operates as follows. When starting solid propellant rocket igniter 11, ignite (almost simultaneously) charge 9 and additional charge 10 (if any). When the expiration of the combustion products through the nozzle 6 creates a thrust. The internal cavity of a working solid propellant rocket motor (body 1 and receiver 3) is loaded with high pressure of combustion products. Due to the smooth conjugation of the axisymmetric nozzle flanges 5 with the sphere of the receiver 3, a significant concentration of stresses in the receiver 3 and nozzle flanges 5 does not occur when loading with internal pressure.

Technical and economic efficiency of the invention, in comparison with the prototypes, which are selected as the central solid propellant rocket engine ДУ САС of the Soyuz-TM spacecraft [On the life and work of Academician B. P. Zhukov. - Tula: Grif and K, 2008. - 304 p., Ill., Pages 79, 80], consists in reducing the mass of the structure and dimensions of the solid propellant rocket engine, simplifying manufacturing technology and improving the quality of manufacturing solid rocket motor.

Claims (3)

1. A solid propellant rocket engine (RDTT) comprising a housing interfaced with a mounting frame, a receiver connected to the housing, the receiver provided with four nozzle flanges, the axes of which are perpendicular to the longitudinal axis of the solid propellant rocket and to each other, four nozzles attached to the nozzle flanges charge, igniter, characterized in that the housing and the receiver are made spherical, and the radius of the receiver is smaller than the radius of the housing, while the charge is firmly bonded to the housing and has a central channel, and the magnitude of the burning arch of the charge is greater and and equal to the difference between the inner radius of the housing and an inner radius of the fastening of the body frame. 2. The rocket engine of solid fuel (RDTT) according to claim 1, characterized in that the protrusions are made on the central charge channel. 3. The solid propellant rocket engine (RDTT) according to claim 1, characterized in that the receiver has an additional charge.

Images