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Copyright of Nonferrous Metals Engineering is the property of Beijing Research Institute of Mining & Metallurgy Technology Group and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Journal of Ordnance Equipment Engineering is the property of Chongqing University of Technology and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Journal of Ordnance Equipment Engineering is the property of Chongqing University of Technology and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

The design of spacecraft servo mechanism plays an important role in the control of the spacecraft. The research of control algorithm and the construction of simulation platform have important practical value. This paper modelles and simulates the mechanical, electrical, hydraulic parts of the aerospace servo mechanism. The overall model of the whole servo system is established. The mechanical structure of the servo mechanism is built in ADAMS and the hydraulic module is built by AMESim. Based on HM theory, the robust controller is built with Matlab toolbox. Combined with the dynamics model of ADAMS and AMESim, as well as the Matlab controller model, the joint simulation of each module is realized. Through the joint simulation technology, the simulation of physical system is more realistic, and the experimental results are also displayed more intuitively. This simulation has a good guiding significance for the design and construction of actual spacecraft servo mechanism system. [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]