Bonding structure and bonding method for double-layer shell of medium-and-small-caliber solid rocket engine
By adopting a double-layer shell bonding structure in a small-diameter solid rocket engine, the shell is divided into the front section and the rear section of the nozzle. Through bonding connection, the phase control problem of the elastic wing and the rudder wing is solved, achieving the purpose of lightweight and simplifying assembly.
CN119712681AInactive Publication Date: 2025-03-28NANJING UNIV OF SCI & TECH
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Patent Information
- Application Number
- CN202411939330.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-26
- Publication Date
- 2025-03-28
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
Technical Problem
The prior art is difficult to accurately control the phase relationship between the wing and the rudder wing in small-caliber solid rocket engines, and there are problems of weight increase and assembly complexity.
Method used
The double-layer shell bonding structure is adopted to divide the engine shell into the front section and the rear section of the nozzle, and is connected through bonding to reduce the connection points and fasteners and simplify the assembly process.
Benefits of technology
It realizes more precise control of the phase relationship between the ammunition wing and the rudder wing, reduces the overall weight of the engine, simplifies the assembly process, and improves production efficiency.
✦ Generated by Eureka AI based on patent content.
Abstract
The invention discloses a bonding structure and a bonding method for a double-layer shell of a medium and small caliber solid rocket engine, and the bonding structure divides an engine shell structure into two parts, and comprises an engine shell front section and an engine shell spray pipe rear section; the engine shell spray pipe rear section comprises a spray pipe and a rear section shell tail pipe. The outer wall of the front section of the engine shell is adhered to the inner wall of the rear section of the spray pipe of the engine shell; compared with the prior art, the double-layer shell bonding structure not only can more accurately control the phase positions of the missile wing and the rudder wing in the circumferential direction of the missile body, but also can reduce the overall weight of an engine to the maximum extent, and the purposes of light weight and miniaturization are achieved.
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