›› 2010, Vol. 30 ›› Issue (6): 49-56.

• 技术交流 • 上一篇    下一篇

铰链展开式构型航天器设计及其动力学仿真

马尚君, 刘更, 罗浩   

  1. (西北工业大学机电学院,西安 710072)
  • 收稿日期:2010-04-13 修回日期:2010-06-18 出版日期:2010-12-25 发布日期:2010-12-25
  • 通讯作者: 马尚君 现为西北工业大学机械专业博士研究生。
  • 作者简介:马尚君 1980年生,2008年获西北工业大学机械专业硕士学位,现为西北工业大学机械专业博士研究生。研究方向为航天器结构机构优化设计及其动力学分析。

Design and Dynamic Simulation of Hinged Deployable Configuration Spacecraft

MA  Shang-Jun, LIU  Geng, LUO  Hao   

  1. (School of Mechatronical Engineering, Northwestern Polytechnical University, Xi'an 710072)
  • Received:2010-04-13 Revised:2010-06-18 Online:2010-12-25 Published:2010-12-25

摘要: 基于航天器结构的模块化设计概念,设计了一种空间可展开航天器模块化结构构型,即铰链展开式构型。利用虚拟样机技术,建立了模块化本体和太阳翼虚拟样机模型。在空间失重环境下,分析了模块化本体和太阳翼在3种展开顺序下(本体各模块和太阳翼同时展开、太阳翼先展开本体各模块后展开和本体各模块先展开太阳翼后展开)对航天器姿态的影响,同时对比了不同扭簧参数对姿态角和展开时间的影响。仿真结果表明该模型可为未来高机动、多型态、多用途自适应变构型航天器的设计以及空间姿态控制提供技术支持和借鉴。

关键词: 模块化设计, 铰链连接, 展开机构, 太阳翼, 姿态控制, 动力学仿真, 航天器设计

Abstract: Based on modular design idea of the spacecraft structure, a hinged deployable configuration for the spacecraft was designed. The virtual prototyping model of modular body and solar panels was established with virtual prototyping technology. And the influence of three deployment sequences of modular body and solar panels on attitude of the spacecraft in the weightless space environment were analyzed, including the modular body and solar panels deployed simultaneously, the modular body deployed after the solar panels, and the solar panels deployed after  the modular body.  Meanwhile, the influences of different torsion spring parameters on attitude angle and deployment time were compared.

Key words: Modular design, Hinge connection, Deployable mechanism, Solar sail, Attitude control, Dynamic simulation, Spacecraft design