Locally-inward-convex spinning shell of solid-propellant rocket engine

Abstract

The invention relates to a locally-inward-convex spinning shell of a solid-propellant rocket engine. The locally-inward-convex spinning shell of the solid-propellant rocket engine comprises a shell body, and an inner convex body is arranged on the inner side surface of the shell body. The shell body is of a tubular structure, the inner convex body penetrates through the shell body in the axial direction of the shell body, the thickness of the inner convex body is larger than the thickness of the shell body, and the inner convex body is connected with the shell body through inclined edges withthe same angles on the two sides. The locally-inward-convex spinning shell of the solid-propellant rocket engine can improve interchangeability and production efficiency of the spinning shell, reduceflight resistance and aerodynamic heating degree of a missile, increase flight speed of the missile, reduce negative quality of the engine and improve the mass ratio of the engine.

Description

technical field [0001] The invention relates to a component of a rocket motor, in particular to a partially inwardly convex solid rocket motor spinning casing. Background technique [0002] The combustion chamber casing is one of the important parts in the engine structure. It is a storage tank filled with solid propellant, a place where the propellant burns, and it is also a component of the missile body. Under the premise of satisfying the requirements of the engine development mission statement, in the design of the engine combustion chamber shell, the various load requirements during the flight test should be considered in the structural design, and the reliable connection of the front and rear compartments should be ensured to improve the reliability of the overall structure of the missile. sex. [0003] The spinning shell of the existing combustion chamber shell mainly adopts the structural form of constant thickness or convex variable thickness. Because the spinning ...

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Problems solved by technology

[0003] The spinning shell of the existing combustion chamber shell mainly adopts the structural form of constant thickness or convex variable thickness. Because the spinning shell of the constant thickness structure adopts the same wall thickness, there are large negative mass, low raw material utilization rate, and engine quality. Disadvantages such as low ratio; although the convex variable thickness structure has a certain improvement on the basis of the constant thickness structure, that is, the wall thickness of the spinning shell foundation is reduced, and only a certain thickness is convex along the axial direction at the welding part of the external parts. reinforcement, such as figure 1 shown

However, due to the difference in the position and quantity of the convex parts, it can only be produced by the positive spinning process with a limited processing length in a single process, and the interchangeability of the spinning shell is poor, and the production efficiency is low; at the same time, because the convex structure increases The diameter of the engine leads to increased aerodynamic resistance and severe local aerodynamic heating under the condition of high-speed flight of the missile, which is not conducive to further increasing the flight speed of the missile

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