Launch vehicle low-temperature composite storage tank with triangular sandwich wall and processing method of tank

Abstract

The invention provides a launch vehicle low-temperature composite storage tank with a triangular sandwich wall. The storage tank comprises a front bottom cover, a front sealing head, a tank cylinder section inner wall, a tank cylinder section outer wall, a rear sealing head, a rear bottom cover and a rear bottom tank housing and is characterized in that a triangular sandwich wall structure comprising reinforcing ribs is arranged between the tank cylinder section outer wall and the tank cylinder section inner wall; and Y ring triangular sandwich wall connecting structures are formed at connecting parts between the front sealing head and the tank cylinder section inner wall, between the front sealing head and the tank cylinder section outer wall, between the rear sealing head and the tank cylinder section inner wall and between the rear sealing head and the tank cylinder section outer wall. The invention further discloses a processing method of the storage tank, which employs an integral co-bonding forming technology of fiber winding forming combined with fiber laying forming. According to the storage tank, the triangular sandwich wall structures are arranged at the high shear stress connecting parts between the sealing heads and a tank cylinder section; the shear strength of the connecting parts is improved; and the storage tank has the effects that the axial carrying capacity of the storage tank is improved, the structure assembly complexity is reduced, and the production efficiency is improved.

Description

technical field [0001] The invention relates to a low-temperature liquid storage tank and a processing method thereof, in particular to a launch vehicle low-temperature composite material storage tank with a triangular sandwich wall, which can replace the traditional aluminum-lithium metal storage tank. It is used in the storage of low-temperature propellant in launch vehicles, the connection of front and rear parts, and the maintenance of the complete shape of the projectile body, etc. Background technique [0002] Domestically produced liquid propellant storage tanks generally use metal materials. At present, in order to realize the overall light weight of launch vehicles, the aerospace sector uses advanced aluminum alloys such as aluminum-lithium alloys with high specific strength and high specific stiffness. [1] . The manufacturing process of metal tanks is generally as follows: a mechanically or chemically milled grid-shaped metal plate is machined and filled with poly...

AI Technical Summary

Problems solved by technology

Therefore, the main defects of traditional metal storage tanks are: large structural mass, complex and diverse processes, long manufacturing cycle, and high cost

[0005] The above three processes alone have the following defects: defects of hand lay-up: low production efficiency; difficult to control product quality, poor performance stability; low fiber content in the product, poor mechanical properties

Defects of filament winding molding: winding molding has little adaptability, and products of any structural form cannot be wound; winding molding requires winding machines, mandrels, curing heating furnaces, demoulding machines and skilled technical workers, which are expensive and require high technology [3]

[0007] When the commonly used single-wall barrel-shaped composite storage tanks work in complex environments, due to the influence of thermal-mechanical coupling loads, high shear stress will be generated at the connection between the head section and the tank section, resulting in Progressive failure of the tank structure, resulting in the leakage of propellant in the tank

Moreover, the storage tank will be subjected to a large axial load during the rocket launch process. The 0° layup in the box section is effective in bearing the axial load, but the winding process cannot wind the 0° layup, so it is necessary to increase the composite material storage. The number of plies with small angles in the tank section, which will lead to a large overall weight of the tank, making it difficult to meet the aerospace weight index

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