RU2229617C1 - Solid-propellant rocket engine - Google Patents

Abstract

FIELD: rocketry. SUBSTANCE: proposed solid-propellant rocket engine contains housing, solid propellant charge, nozzle unit, igniter, sealing-and-starting unit and cartridge. Sealing-and-starting unit has member made in form of several telescopic ring bushi9ngs interconnected by spline joint and installed for axial displacement relative to each other direction of powder gases flow. Cartridge is arranged in central ring bushing connected by reheat tube with fitted-on support resting on subsonic part of nozzle. EFFECT: reduced spread of reheat pressure and dispersion of rocket trajectory, improved manufacturability of rocket engine and reliability of rocket as a whole. 2 dwg

Description

The invention relates to the field of rocketry and is intended for use in missiles for various purposes, including missiles of multiple launch rocket systems.

One of the main tasks to be solved when designing solid propellant rocket engines is to ensure reliable sealing of its combustion chamber during storage and switching on when an electroflamer is activated.

The design of a solid fuel rocket engine is known, in which the launch unit is located on the front bottom, and a sealing plug is installed in the nozzle block (see B.T. Erokhin, A.M. Lipatov. Transient and quasistationary modes of operation of solid propellant rocket motors. - M.: Mechanical Engineering , 1977, p.5, fig.1.1)

Thus, the objective of this technical solution was the development of starting and sealing units for a rocket engine of solid fuel.

Common signs with the solid fuel rocket engine proposed by the authors is the presence in it of a housing, a charge of solid fuel, a sealing and launching unit, as well as a squib.

However, the above design of a solid fuel rocket engine has drawbacks in that the engine start is accompanied by a significant "peak" pressure of gaseous products in the combustion chamber, causing a decrease in the mass perfection coefficient of the design.

These disadvantages are deprived of a solid fuel rocket engine, in which the launch unit is located in the nozzle block.

The closest in technical essence and the technical result achieved is a solid fuel rocket engine containing a casing, a solid fuel charge, a nozzle block, an igniter, a sealing-launch unit and a squib (see A.M. Lipatov, A.V. Aliyev. Design of rocket solid fuel engines. - M.: Mechanical Engineering, 1995, p. 241, Fig. 7.15.b), adopted by the authors for the prototype.

As can be seen from this technical solution, the sealing-starting unit and the squib are fixed in the nozzle block, which allows the engine to be started under conditions when most of the fuel combustion surface is in the vicinity of the nozzle.

A known engine operates as follows. After the igniter is activated and the solid fuel charge is ignited, a sharp increase in pressure in the combustion chamber of the engine occurs.

Upon reaching the predetermined boost pressure of the solid fuel rocket engine, the fastening elements of the sealing unit are destroyed and removed from the engine nozzle. At the same time, unburned powder particles are removed from the combustion chamber from the igniter, which eliminates the occurrence of a “peak” gas pressure in the combustion chamber. At the same time, during the exit of the sealing start-up assembly from the nozzle, an increased dispersion of the boost pressure is observed, which is explained by the skew of this assembly in the nozzle block under the influence of a gas-dynamic impact of combustion products and elastoplastic, asymmetric deformations of the fastening elements of the sealing start-up assembly. Moreover, the magnitude of the pressure dispersal forcing depends on the caliber of the rocket engine and its design features. In addition, the distortions of the sealing-starting unit in the nozzle hole at the time of starting the rocket engine can lead to collisions and damage to the nozzle path, which is unacceptable when using shock-sensitive plastic or graphite-containing heat-shielding materials. These shortcomings lead to significant dispersion in range, which significantly reduces the possibility of hitting point targets and requires increased missile consumption to ensure that they effectively hit enemy targets.

Thus, the objective of this technical solution (prototype) was to create the design of a rocket engine of solid fuel, which allows to reduce the peak pressure of the combustion products in the combustion chamber at the time of launch.

Common features with the device proposed by the authors is the presence in the rocket engine of solid fuel of the housing, nozzle block, igniter, sealing-launching unit and squib.

In contrast to the prototype, in the rocket engine proposed by the authors, the sealing-launching unit contains a plate made in the form of several telescopic ring bushings fastened together by means of a spline connection and mounted with the possibility of sequential axial movement relative to each other in the direction of expiration of the powder gases, while the squib is placed in the central annular sleeve connected by an afterburner with a support fixed to it, resting on the subsonic part of the nozzle.

It is this that allows us to conclude that there is a causal relationship between the totality of the essential features of the claimed technical solution and the achieved technical result.

These signs, distinctive from the prototype and to which the requested amount of legal protection applies, are sufficient in all cases.

The task of the invention is to reduce the pressure spread of boosting and increase the reliability and manufacturability of manufacturing a rocket engine of solid fuel.

The specified technical result during the implementation of the invention is achieved by the fact that in the known rocket engine containing a solid fuel charge, nozzle block, igniter, sealing-launching unit and squib, the feature is that the sealing-starting unit contains a plate made in the form several telescopic ring bushings, fastened together by means of a spline connection and mounted with the possibility of sequential axial movement relative to each other in the direction the outflow of powder gases, while the squib is placed in the Central annular sleeve connected by an afterburner with a support fixed to it, resting on the subsonic part of the nozzle.

A new set of structural elements, as well as the presence of connections between them, allow, in particular, due to:

- making plates in the form of several telescopic ring bushings fastened together by means of a spline connection and having the possibility of sequential axial movement relative to each other in the direction of gas outflow, to eliminate the asymmetry of the gas thermodynamic effect of the jet of combustion products of the igniter on the surface of the igniter body, to increase the exposure time of the jet of combustion products of the initiator the composition of the igniter on the igniter, to ensure the stability of the ignition process a measurer and thereby reduce the pressure spread in the engine;

- placing the pyro cartridge in the central annular sleeve connected by the afterburner with a support mounted on it, resting on the subsonic part of the nozzle, to increase the manufacturability, as well as to ensure the alignment of the afterburner and the nozzle block during operation of the igniter, to significantly reduce the dispersion of the breakdown force of the sealing unit while eliminating unsteady oscillations of the specified jet on the surface of the igniter body in the zone of their interaction and to increase the reliability of the engine.

Signs that distinguish the proposed technical solution from the prototype are not identified in other technical solutions and are not known from the prior art in the process of conducting patent research, which allows us to conclude that the invention meets the criterion of “novelty”.

Studying the level of technology during the patent search on all types of information available in the countries of the former USSR and foreign countries, it was found that the proposed technical solution clearly does not follow from the prior art, therefore, we can conclude that the criterion of "inventive step" is met.

The essence of the invention lies in the fact that the rocket engine of solid fuel, comprising a housing, a charge of solid fuel, a nozzle block, an igniter, a sealing-starting unit and a squib, according to the invention, the sealing-starting unit contains a plate made in the form of several telescopic ring bushings fastened between by means of a spline connection and mounted with the possibility of sequential axial movement relative to each other in the direction of flow of the powder gases, with pyrope the atron is located in the central annular sleeve connected by an afterburner with a support fixed to it, resting on the subsonic part of the nozzle.

The invention is illustrated in the drawing, where figure 1 shows a longitudinal section of a rocket engine of solid fuel, figure 2 is a longitudinal section of the tail of the rocket engine.

The proposed solid fuel rocket engine comprises a housing 1, in which a solid fuel charge 2 is placed, an igniter 3 fixed in a pre-nozzle volume, a nozzle block 4 and a sealing-starting device 5 installed in the pre-nozzle volume, which includes a support 6 supported by a subsonic (input) part nozzle 14, plate 7, made in the form of several telescopic ring bushings 8, 9, 10 and mounted in the supersonic part of the nozzle 14, while the support 6 is connected to the plate 7 using a nut 11 screwed on the afterburner the flange 12, fastened on the opposite side to the central annular sleeve 10, in which the squib 13 is mounted.

The above device operates as follows.

After applying an electric pulse to the igniter 13, the combustion products of the initiating composition move inside the afterburner 12 and, after exiting from the opposite side, ignite the powder composition of the igniter 3, which, in turn, ignites the charge of solid fuel 2. Under the influence of the pressure of the powder gases generated in the combustion chamber housing 1, the deformation of the support 6 occurs and the movement of the telescopic annular sleeves 8, 9, 10 of the plate 7 relative to the nozzle 14 in the direction of expiration of the powder gases begins. In the process of starting a rocket engine, the support 6 holds the afterburner 12 along the axis of the nozzle block 4, including during its deformation, excluding distortions and collision of the afterburner 12 with the walls of the nozzle 14. When the telescopic bushings 8, 9, 10 of the plate are mutually sequentially moved 7 the opposite end of the afterburner tube 12 is moved along the axis of the nozzle 14, which allows to increase the time of exposure to the combustion products of the initiating composition of the igniter 13 with the igniter 3. No distortion of the sealing-starting device Twa 5 relative to the nozzle block 4 axis during launch rocket engine minimizes boost pressure variation in the combustion chamber formed by the housing 1 and the nozzle unit 4.

The implementation of the rocket engine of solid fuel in accordance with the invention allowed to reduce the dispersion of the pressure of forcing, to reduce the technical dispersion of the trajectory of the rocket, as well as to improve the manufacturability of the rocket engine and the reliability of the rocket as a whole.

The invention can be used in the development of various solid propellant rocket engines, including rockets for multiple launch rocket systems.

The indicated positive effect is confirmed by tests of prototypes of engines made in accordance with the invention.

Currently, design documentation has been developed, state tests have been carried out, and mass production is scheduled.

Claims (1)

A rocket engine of solid fuel, comprising a housing, a charge of solid fuel, a nozzle block, an igniter, a sealing-launching unit and a squib, characterized in that the sealing-starting unit contains a plate made in the form of several telescopic ring bushings fastened together by means of a spline connection and mounted with the possibility of sequential axial movement relative to each other in the direction of the outflow of powder gases, while the squib is placed in the Central annular sleeve ke connected by means of an afterburner with a support fixed on it, resting on the subsonic part of the nozzle.

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