Zero-expansion dot matrix cylindrical shell structure used for spacecraft and design method thereof

Abstract

The invention discloses a zero-expansion dot matrix cylindrical shell structure used for a spacecraft and a design method thereof. According to the zero-expansion dot matrix cylindrical shell structure, a zero-expansion planar structure (5) is curved to form a cylinder, the zero-expansion planar structure (5) is obtained by spatially translating and interconnecting multiple zero-expansion basic cells (4) on a plane, each zero-expansion basic cell (4) is obtained by connecting four same micro-structures(3) at a top point, every two adjacent micro-structures (9) in each basic cell (4) are perpendicular to each other, and each micro-structure (3) is a triangle composed of a bottom edge (1) and two bevel edges (2). When the zero-expansion dot matrix cylindrical shell structure is designed, two different types of metal materials are selected to respectively serve as the material of the bottom edges (1) and the material of the bevel edges (2); then geometric dimension of the microstructure (3), the height and diameter of the zero-expansion dot matrix cylindrical shell structure (6), the number of basic cells in the annular direction, the number of basic cells in the height direction, the length of each bottom edge (1), the length of each bevel edge (2) and the section shape are designed in sequence; a finite element method is adopted for simulation; and a final design scheme is obtained through adjusting the length of each bottom edge (1) and the length of each bevel edge (2).

Description

technical field [0001] The invention belongs to the field of machinery, and relates to a cylindrical shell structure for spacecraft and a design method thereof. The cylindrical shell structure has the characteristics of "zero expansion" in radial direction and height direction at the same time, and is suitable for payloads such as cameras or antennas of spacecraft The support structure and space on-orbit assembly structure, etc. Background technique [0002] Spacecraft usually use lightweight alloys and composite materials to meet the mechanical performance requirements such as stiffness and strength of structural design. At present, honeycomb sandwich panels have been widely used in the design of spacecraft structures, and lattice structures are considered to be a new generation of lightweight materials with good application prospects. The lattice structure design conforms to the collaborative optimization design concept of integrating material design, structure design and...

AI Technical Summary

Problems solved by technology

However, the currently widely used fiber-reinforced composite materials have the following disadvantages: 1) poor thermal conductivity, which is not conducive to temperature control of thermal control equipment; Deterioration; 3) The process stability is poor, and the material performance is scattered

As a result, the actual performance of the product is quite different from the design value

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