CN113153580A

CN113153580A - Combined spray pipe of solid rocket engine

Info

Publication number: CN113153580A
Application number: CN202110355093.XA
Authority: CN
Inventors: 张群; 王晓燕; 马晓曦; 王紫欣; 高耀红
Original assignee: Northwestern Polytechnical University
Current assignee: Northwestern Polytechnical University
Priority date: 2021-03-31
Filing date: 2021-03-31
Publication date: 2021-07-23
Anticipated expiration: 2041-03-31
Also published as: CN113153580B

Abstract

The invention provides a combined type spray pipe of a solid rocket engine, and relates to the technical field of solid rocket engines. The invention improves on the basis of the conventional tail nozzle, skillfully combines the single-sided expansion nozzle and the Laval nozzle, and simultaneously exerts the advantages of the two nozzles. In the invention, an asymmetric single-bevel expansion nozzle is specifically adopted, a convergent section of the nozzle is fixed and connected with the wall surface of a combustion chamber, and an expansion section is connected with a flexible joint to form a movable part which can swing within a certain angle, so that vector thrust within a larger range is generated, and vector control on a solid rocket engine is completed. In order to solve the flow loss generated by the single-bevel expansion nozzle, the Laval nozzle is arranged in the single-bevel expansion nozzle, so that the full expansion acceleration of gaseous combustion products can be realized, and the energy conversion can be efficiently completed. The combination of the two nozzles can realize that vector thrust in a larger range can be generated under the condition of smaller flow loss, so that the control on the flight direction of the solid rocket engine is improved.

Description

Combined spray pipe of solid rocket engine

Technical Field

The invention belongs to the technical field of solid rocket engines, and particularly relates to a combined type spray pipe of a solid rocket engine.

Background

The solid rocket engine is a solid propellant rocket engine for short, and mainly comprises a combustion chamber shell solid propellant charge, a spray pipe, an ignition device and the like. In solid rocket engines, the propellant for combustion is pressed or cast into a charge of desired shape, which is directly placed in the combustion chamber or engine casing. Solid rocket engines are used in a variety of aircraft: ballistic missiles, space systems and launch vehicles, cruise missiles and aircraft, and ground-to-air and air-launched missile systems.

The solid rocket engine may be used as the main engine of the rocket, or as an auxiliary engine for flight control interstage and head separation, braking and soft landing, spacecraft emergency rescue, and pilot-specific compartments. The main structural parts of the solid rocket engine are a shell, a spray pipe, a grain, a starting system, a thrust stopping (stopping) device, an emergency engine shutdown device, an auxiliary device and the like. The solid rocket engine with motion control function used in aircraft has special control mechanism for changing the magnitude and direction of thrust vector. To control the direction of the thrust vector, a main nozzle of the engine or a gas jet device producing a local effect may be utilized.

The jet pipe is an important component of the solid rocket engine, and the design quality of the jet pipe determines the main propelling performance of the engine. In order to achieve better internal performance of the spray pipe, the invention optimizes the structure of the spray pipe, combines two different types of spray pipes and realizes vector control on the engine under the condition of meeting the maximum expansion ratio.

Disclosure of Invention

The invention aims to solve the technical problem of providing a combined nozzle of a solid rocket engine, so as to solve the problem that the expansion ratio and the vector control of the nozzle at the present stage are difficult to be compatible. In the technology, the single-bevel expansion nozzle is combined with the Laval nozzle, wherein the convergent section and the divergent section of the single-bevel expansion nozzle are connected through a flexible joint, so that the vector control of the solid rocket engine can be realized within a larger swing angle range; the inner Laval nozzle compensates for the loss of the outer single-bevel expansion nozzle in the flow process, so that the maximum expansion ratio of the combined nozzle can meet the design requirement. Inlets of the single-bevel expansion nozzle and the Laval nozzle are respectively connected with outlets of the outer ring gas channel and the inner ring gas channel, so that the gaseous combustion products generate vector thrust while being fully expanded and accelerated.

Technical scheme

The invention aims to provide a combined nozzle of a solid rocket engine.

The technical scheme of the invention is as follows:

a combined nozzle of a solid rocket engine is characterized in that: the solid rocket engine combustion chamber grain adopts a double-ring tubular grain with an inner hole for combustion, and the spray pipe adopts a combined structure of a single-inclined-plane expansion spray pipe and a Laval spray pipe; the convergent section of the single-bevel expansion nozzle is a fixed part, the expansion section is a movable part which can swing in a point range, and the two are connected by a flexible joint to generate vector thrust; the interior of the expansion nozzle is provided with a Laval nozzle which is integrally fixed and used for compensating the flow loss generated by the single-inclined-plane expansion nozzle.

The combined type spray pipe of the solid rocket engine is characterized in that: the inlet of the convergent section of the inner Laval nozzle is connected with the outlet of the inner ring fuel gas channel, and the central lines of the inner Laval nozzle and the inner ring fuel gas channel are on the same straight line.

The combined type spray pipe of the solid rocket engine is characterized in that: the single-bevel expansion nozzle is arranged on the outer side of the Laval nozzle, the inlet of the convergent section of the single-bevel expansion nozzle is connected with the outlet of the outer ring fuel gas channel, and the central lines of the single-bevel expansion nozzle, the convergent section of the single-bevel expansion nozzle and the outer ring fuel gas channel are located on the same straight line.

The combined type spray pipe of the solid rocket engine is characterized in that: the air flow channel between the two nozzles still follows the principle of converging first and then diverging, and the throat position of the air flow channel is approximately the same as that of the Laval nozzle. .

The invention has the following beneficial effects:

(1) the invention is optimized and improved on the basis of the existing spray pipe, and the combined spray pipe is adopted, so that the maximum expansion ratio of the spray pipe is met, and simultaneously, the vector thrust is generated. (2) The convergent section and the expansion section of the single-bevel expansion nozzle are connected through the flexible joint, and the expansion section can rotate and deflect a certain angle according to a control instruction, so that the thrust direction is changed, and the vector control of the solid rocket engine is realized. (3) The Laval nozzle is fixed in the single-bevel expansion nozzle, so that various losses of the single-bevel expansion nozzle caused by incomplete expansion, diffusion, chemical kinetics, friction and the like can be compensated, and the complete expansion and acceleration processes of gaseous combustion products can be realized at the position.

Drawings

FIG. 1: sectional view of combined nozzle of solid rocket engine

FIG. 2: schematic diagram of combined spray pipe of solid rocket engine

FIG. 3: 3/4 schematic diagram of combined nozzle of solid rocket engine

In the figure: 1-combustion chamber wall surface, 2-outer ring tubular grain, 3-inner ring tubular grain, 4-convergence section of single inclined plane expansion nozzle, 5-flexible joint, 6-expansion section of single inclined plane expansion nozzle, and 7-Laval nozzle.

Detailed Description

The invention will now be further described with reference to the accompanying drawings in which:

referring to fig. 1, the present invention provides a combined nozzle of a solid rocket engine generating a vectored thrust while securing a maximum expansion ratio.

The specific process comprises the following steps:

the design limit is definite, and the spray pipe in the invention adopts a mode of combining a single-bevel expansion spray pipe and a Laval spray pipe 7. The outer ring tubular grain 2 is burnt, and gaseous combustion products flow to a convergent section 4 of the single-bevel expansion nozzle from the outer ring gas channel, and the section is fixed and connected with the wall surface 1 of the combustion chamber to play a stabilizing role; the convergent section 4 and the divergent section 6 are connected by a flexible joint 5, so that the divergent section 6 of the single-bevel expansion nozzle can swing within a certain angle range, thereby changing the exhaust direction of high-sonic-velocity gas, generating vector thrust within a larger range and realizing vector control on the solid rocket; the inner channel of the single-bevel expansion nozzle consists of the inner wall surface of the single-bevel expansion nozzle and the outer wall surface of the Laval nozzle, and follows the principle of contraction before expansion, so that the action on the gas is similar to that of the common single-bevel expansion nozzle. Although the propulsion system is simple, the system has great asymmetry in the pitching direction and may generate various losses in the air flow process, such as incomplete expansion and the like, so the invention adds the Laval nozzle 7 to compensate the corresponding losses. The inner ring tubular explosive column 3 burns simultaneously, the gaseous product flows to the Laval nozzle 7 from the inner ring gas channel, the combustion product is continuously expanded and accelerated, the maximum expansion ratio of the combined nozzle meets the requirement, and meanwhile, the heat energy is converted into kinetic energy, so that the solid rocket does propelling work.

Claims

1. A combined nozzle of a solid rocket engine is characterized in that: the solid rocket engine combustion chamber grain adopts a double-ring tubular grain with an inner hole for combustion, and the spray pipe adopts a combined structure of a single-inclined-plane expansion spray pipe and a Laval spray pipe; the convergent section of the single-bevel expansion nozzle is a fixed part, the expansion section is a movable part which can swing in a point range, and the two are connected by a flexible joint to generate vector thrust; the interior of the expansion nozzle is provided with a Laval nozzle which is integrally fixed and used for compensating the flow loss generated by the single-inclined-plane expansion nozzle.

2. The modular nozzle of a solid-rocket engine as recited in claim 1, wherein: the inlet of the convergent section of the inner Laval nozzle is connected with the outlet of the inner ring fuel gas channel, and the central lines of the inner Laval nozzle and the inner ring fuel gas channel are on the same straight line.

3. The modular nozzle of a solid-rocket engine as recited in claim 1, wherein: the single-bevel expansion nozzle is arranged on the outer side of the Laval nozzle, the inlet of the convergent section of the single-bevel expansion nozzle is connected with the outlet of the outer ring fuel gas channel, and the central lines of the single-bevel expansion nozzle, the convergent section of the single-bevel expansion nozzle and the outer ring fuel gas channel are located on the same straight line.

4. The modular nozzle of a solid-rocket engine as recited in claim 1, wherein: the air flow channel between the two nozzles still follows the principle of converging first and then diverging, and the throat position of the air flow channel is approximately the same as that of the Laval nozzle.