阅读说明：本技术 一种微动力固体火箭发动机燃烧室壳体粘接结构 (Micro-power solid rocket engine combustion chamber shell bonding structure ) 是由 陈国栋 马海波 邓斌 于 2021-07-22 设计创作，主要内容包括：本发明涉及到固体火箭发动机设计制造技术,具体涉及一种微动力固体火箭发动机燃烧室壳体粘接结构。包括燃烧室壳体前段、燃烧室壳体喷管后段,所述燃烧室壳体前段1与燃烧室壳体喷管后段2连接处采用胶粘接而成。所述燃烧室壳体前段1外壁和燃烧室壳体喷管后段2内壁相粘接成为固体火箭发动机燃烧室。本发明避免了采用其它连接方式导致的单个零部件加工,导致的应力集中,强度不均等问题,本发明将大大降低甚至取消了对后期总装装配工装的依赖,简化了工艺流程,尤其对批生产的发动机,生产效率将得到很大提升,有效的保证了产品的外观不受损伤,提高了产品的外观质量性能。(The invention relates to a solid rocket engine design and manufacture technology, in particular to a micro-power solid rocket engine combustion chamber shell bonding structure. The combustor casing jet pipe comprises a combustor casing front section and a combustor casing jet pipe rear section, wherein the joint of the combustor casing front section 1 and the combustor casing jet pipe rear section 2 is formed by gluing. The outer wall of the front section 1 of the combustion chamber shell and the inner wall of the rear section 2 of the spray pipe of the combustion chamber shell are bonded to form the combustion chamber of the solid rocket engine. The invention avoids the problems of stress concentration, uneven strength and the like caused by processing of single parts by adopting other connection modes, greatly reduces or even cancels the dependence on final assembly and assembly tools, simplifies the process flow, greatly improves the production efficiency especially for mass production engines, effectively ensures that the appearance of the product is not damaged, and improves the appearance quality performance of the product.)

1. A micro-power solid rocket engine combustion chamber shell bonding structure is characterized in that: the combustor casing jet pipe comprises a combustor casing front section (1) and a combustor casing jet pipe rear section (2), wherein the joint of the combustor casing front section (1) and the combustor casing jet pipe rear section (2) is formed by gluing.

2. The bonding structure of the combustion chamber housing of a micro-power solid rocket engine according to claim 1, wherein: the combustion chamber housing is machined from soft and light aluminum.

3. The bonding structure of the combustion chamber housing of a micro-power solid rocket engine according to claim 1, wherein: the front section (1) of the combustion chamber shell and the rear section (2) of the spray pipe of the combustion chamber shell are formed by machining.

4. The bonding structure of the combustion chamber housing of a micro-power solid rocket engine according to claim 1, wherein: the outer wall of the front section (1) of the combustion chamber shell and the inner wall of the rear section (2) of the spray pipe of the combustion chamber shell are bonded to form the combustion chamber of the solid rocket engine.

5. The bonding structure of the combustion chamber housing of a micro-power solid rocket engine according to any one of claims 1-4, wherein: the thickness of the mutual bonding part of the front section (1) of the combustion chamber shell and the rear section (2) of the spray pipe of the combustion chamber shell is half of the design thickness of the combustion chamber shell of the engine, and a glue coating gap is processed and reserved.

Technical Field

The invention relates to a solid rocket engine design and manufacture technology, in particular to a micro-power solid rocket engine combustion chamber shell bonding structure.

Background

Due to the particularity of the solid rocket engine, the assembly of the engine is manual operation, the micro engine is limited in size and simultaneously considers the problem of mass ratio, and the combustion chamber shell is made of soft and light (relative to steel materials) aluminum materials. As with other types of engines, the traditional screw threads and other connection modes are adopted, the later assembly efficiency cannot be guaranteed, and the appearance quality is difficult to meet the requirements. Aiming at the problem, the invention provides a bonding structure of a combustion chamber shell of a micro-power solid rocket engine, which divides the combustion chamber shell into two parts and bonds the two parts during assembly, and can replace the traditional threads and other connection modes of a front seal head and the combustion chamber shell. The method can greatly reduce or even cancel the dependence on the final assembly tool, simplify the process flow, greatly improve the production efficiency especially for batch-produced engines, effectively ensure that the appearance of the product is not damaged, and improve the appearance quality performance of the product.

Considering the particularity of the solid rocket engine, the assembly of the existing engine is manual operation, and the consideration of the assembly efficiency and the quality is very important, particularly the assembly of a large-batch micro engine. Because of the limited size of the micro-engine and considering the mass ratio, the combustion chamber housing is made of soft and light (relative to steel) aluminum. Adopt traditional assembly methods, later stage assembly efficiency can't obtain guaranteeing, and appearance quality hardly reaches the requirement.

The existing assembly modes of the existing solid rocket engine are all carried out by adopting traditional threads and other connection modes, the used tools are more during the overall assembly, and in order to ensure the appearance quality of finished products, the assembly must be careful and careful. Even so, the low efficiency and the low appearance yield cannot be avoided.

Because of the size constraints of miniature engines while considering mass ratio issues, the combustion chamber housing is typically made of soft and light (relative to steel) aluminum. The existing traditional threads and other connecting modes are adopted for assembly like other types of engines, the dependence degree on an assembly tool is high, the process flow is complex, the assembly efficiency cannot be guaranteed, and the appearance quality cannot meet the requirements.

The invention aims to provide a novel micro-power solid rocket engine combustion chamber shell bonding structure to improve the efficiency and quality of the production and assembly link of a solid rocket engine. The combustion chamber shell is divided into the front section of the combustion chamber shell and the rear section of the spray pipe of the combustion chamber shell, and the front section and the rear section are only required to be bonded into a whole. By doing so, will greatly reduced even cancelled the reliance to later stage assembly fixture, simplified process flow, especially to the engine of batch production, production efficiency will obtain very big promotion, the effectual outward appearance that has guaranteed the product is not damaged, has improved the appearance quality performance of product.

Disclosure of Invention

Technical problem to be solved by the invention

The invention provides a novel micro-power solid rocket engine combustion chamber shell bonding structure, which is used for improving the efficiency and quality of the production and assembly link of a solid rocket engine.

Technical scheme adopted by the invention for solving technical problem

A bonding structure of a combustion chamber shell of a micro-power solid rocket engine comprises a combustion chamber shell front section 1 and a combustion chamber shell spray pipe rear section 2, wherein the joint of the combustion chamber shell front section 1 and the combustion chamber shell spray pipe rear section 2 is formed by gluing.

Further, the combustion chamber housing is machined from a soft and light aluminum material.

Further, the front section 1 of the combustion chamber shell and the rear section 2 of the nozzle of the combustion chamber shell are formed by machining.

Furthermore, the outer wall of the front section 1 of the combustion chamber shell and the inner wall of the rear section 2 of the jet pipe of the combustion chamber shell are bonded to form the combustion chamber of the solid rocket engine.

Furthermore, the thickness of the mutual bonding part of the front section 1 of the combustion chamber shell and the rear section 2 of the spray pipe of the combustion chamber shell is half of the design thickness of the combustion chamber shell of the engine, and a glue coating gap is processed and reserved.

Advantageous effects obtained by the present invention

The invention avoids the problems of stress concentration, uneven strength and the like caused by processing of single parts by adopting other connection modes, greatly reduces or even cancels the dependence on final assembly and assembly tools, simplifies the process flow, greatly improves the production efficiency especially for mass production engines, effectively ensures that the appearance of the product is not damaged, and improves the appearance quality performance of the product.

Drawings

FIG. 1: a sectional view of a bonding structure of a combustion chamber shell of the micro-power solid rocket engine;

wherein: 1-the front section of the combustion chamber shell and 2-the rear section of the spray pipe of the combustion chamber shell.

Detailed Description

In order to make the objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. It is obvious that the described embodiments are only some, not all embodiments of the proposed solution. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

As shown in figure 1, is a sectional view of a bonding structure of a combustion chamber shell of a novel micro-power solid rocket engine. Comprises two parts, namely a front section 1 of a combustion chamber shell and a rear section 2 of a spray pipe of the combustion chamber shell. The entire combustion chamber housing is typically machined from a soft, lightweight (relative to steel) aluminum material. The front section 1 of the combustion chamber shell and the rear section 2 of the spray pipe of the combustion chamber shell are formed by machining.

Firstly, the thin-wall end of the front section 1 of the combustion chamber shell is abutted against the inner table surface end of the rear section 2 of the spray pipe of the combustion chamber shell, and then the outer wall of the front section 1 of the combustion chamber shell is bonded with the inner wall of the rear section 2 of the spray pipe of the combustion chamber shell to form the combustion chamber of the solid rocket engine. The thickness of the mutual bonding part of the front section 1 of the combustion chamber shell and the rear section 2 of the spray pipe of the combustion chamber shell is half of the design thickness of the combustion chamber shell of the engine, and a glue coating gap is processed and reserved. And calculating the glue smearing amount according to the glue smearing length, and bonding the front section 1 of the combustion chamber shell and the rear section 2 of the spray pipe of the combustion chamber shell into a whole. The selection and use of the colloid need to achieve the following points:

the adhesive needs to be a colloid with good fluidity and high bonding strength after being coated and cured at normal temperature. Coating the colloid on the surface of the shell made of the same material, wherein the coating thickness is designed according to the designed gap of the shell, carrying out a tensile stress verification test after the colloid is cured, and calculating the maximum limit bonding tensile stress of each square centimeter;

the bonding surface is designed with a gap, if the actual glue smearing requirement cannot be met, the wall thickness safety coefficient of the combustion chamber can be reduced, the wall thickness can be calculated, and the fine adjustment is properly carried out, so that the glue smearing gap is increased.

After the tensile stress verification test is completed, taking the safety coefficient of 3-5, and calculating the area of the colloid to be coated under the condition of reaching the safe tensile stress;

dividing the area of the daubing colloid by the circumference of the excircle of the bonding surface at the rear section of the combustion chamber shell to obtain the length of the daubing colloid;

a combustion chamber shell bonding structure of a micro-power solid rocket engine is characterized in that a combustion chamber shell is divided into a front combustion chamber shell section and a rear combustion chamber shell nozzle section, and the front section and the rear section are bonded into a whole to form the combustion chamber of the solid rocket engine. The traditional threads and other connecting modes of the existing front seal head and the combustion chamber shell are replaced, so that the problems that the assembly mode is high in dependence degree on an assembly tool, the process flow is complex, the assembly efficiency cannot be guaranteed, the appearance quality cannot meet the requirement and the like are solved.

The invention greatly reduces or even cancels the serious dependence of the assembly tool on the assembly of the engine combustion chamber shell by adopting the traditional screw thread and other connection modes at present, simplifies the process flow, greatly improves the production efficiency especially for the engines produced in batches, effectively ensures that the appearance of the product is not damaged, and improves the appearance quality performance of the product.

The invention mainly provides a micro-power solid rocket engine combustion chamber shell bonding structure, which divides a combustion chamber shell into two parts, bonds the combustion chamber shell during assembly, and replaces the traditional threads and other connection modes of a front seal head and the combustion chamber shell, thereby avoiding the problems that the connection mode has high dependence on an assembly tool, the process flow is complex, the assembly efficiency cannot be ensured, the appearance quality is difficult to meet the requirement, and the like. The combustion chamber shell is divided into the front section of the combustion chamber shell and the rear section of the spray pipe of the combustion chamber shell, and the front section and the rear section are bonded into a whole to form the combustion chamber of the solid rocket engine. By doing so, will greatly reduced or even cancel the reliance to later stage assembly fixture, simplify process flow, especially to the engine of batch production, production efficiency will obtain very big promotion, the effectual outward appearance that has guaranteed the product is not damaged, has improved the appearance quality performance of product.