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With the increasing demand ol spacecraft lor 3D-printing metal materials, spacecraft propose higher requirements for reliability of 3D-printing metal materials. Based on the analysis results of service environment in spacecraft, the characteristics of 3D-printing materials and the application lunctions in spacecraft, this paper established the properties evaluation technical index system, designed the technical route of scheme and delined the properties index evaluation method Irom the perspective ol 3D-printing metal raw materials, typical components and products. Finally, a technical scheme lor reliability evaluation ol 3D-printing metal materials for spacecraft was lormed, which provided technical support for the sale and reliable application ol 3D-printing materials in the aerospace lield. [ABSTRACT FROM AUTHOR]

The existing maintainable spacecraft costs a lot to realize the maintainability, and the technical development path is not clear, so it is difficult to popularize and apply. Based on the analysis of the technical characteristics of foreign maintainable spacecraft, this paper puts forward a general design method for maintainable spacecraft from three aspects: maintainable architecture, replaceable functional module architecture and plug-and-play interface architecture. Combined with the proposed method, a modular maintainable satellite with variable main structure configuration is designed, and the key technologies involved are described. The designed serviceable satellite takes the open mechanical system with variable configuration, distributed heterogeneous network system and refillable propulsion system as the core architecture, and the two-level functional modules and three-level interfaces as the repairable carrier. It realizes the maintainability at low cost, reduces the capability requirements for maintenance operators, and the system function and performance can evolve dynamically with the technology development. The proposed method and typical design case could provide reference for the development of maintainable spacecraft and corresponding technologies in China. [ABSTRACT FROM AUTHOR]

The Mars flux has great influence on the solar panel temperature. This paper establishes a mathematical model of the Mars albedo flux and analyzes the variation of the solar panel temperature in the near Mars area and the far Mars area when the Mars infrared radiation and the Mars albedo change. The research indicates that the influence are different when the spacecraft is at different orbital heights. There exists a critical orbit height. When the orbit height is less than the critical height, the influence is very large, and when it is great than this critical height, the influence could be ignored. This research provids a reference for the future Mars exploration. [ABSTRACT FROM AUTHOR]