随着科技的不断进步,主要依赖机械技术和电子技术的传统机电支架力学性能分析系统已经不能满足日益增长的需求,无法进行更为庞大的计算及精确的控制能力,鉴于此,通过计算机技术,提出基于MFC框架的机电支架力学性能分析系统。系统开发利...随着科技的不断进步,主要依赖机械技术和电子技术的传统机电支架力学性能分析系统已经不能满足日益增长的需求,无法进行更为庞大的计算及精确的控制能力,鉴于此,通过计算机技术,提出基于MFC框架的机电支架力学性能分析系统。系统开发利用Visual Studio 2015开发平台,Access数据库,软件采用MFC框架。系统经过测试验证,运行稳定,使用效果良好,方便了工程设计人员使用。展开更多
Electrodynamic tethered deorbit technology is a novel way to remove abandoned spacecrafts like upper stages or unusable satellites. This paper investigates and analyses the deorbit performance and mission applicabilit...Electrodynamic tethered deorbit technology is a novel way to remove abandoned spacecrafts like upper stages or unusable satellites. This paper investigates and analyses the deorbit performance and mission applicability of the electrodynamic tethered system. To do so, the electrodynamic tethered deorbit dynamics with multi-perturbation is firstly formulated, where the Earth magnetic field, the atmospheric drag, and the Earth oblateness effect are considered. Then, the key system parameters, including payload mass, tether length and tether type, are analyzed by numerical simulations to investigate their influences on the deorbit performance and to give the setting principles for choosing system parameters. Based on this and given an appropriate group of system parameters, numerical simulations are undertaken to study the impact of the mission parameters, including orbit height and orbit inclination, and thus to investigate the mission applicability of the electrodynamic tethered deorbit technology.展开更多
文摘随着科技的不断进步,主要依赖机械技术和电子技术的传统机电支架力学性能分析系统已经不能满足日益增长的需求,无法进行更为庞大的计算及精确的控制能力,鉴于此,通过计算机技术,提出基于MFC框架的机电支架力学性能分析系统。系统开发利用Visual Studio 2015开发平台,Access数据库,软件采用MFC框架。系统经过测试验证,运行稳定,使用效果良好,方便了工程设计人员使用。
文摘Electrodynamic tethered deorbit technology is a novel way to remove abandoned spacecrafts like upper stages or unusable satellites. This paper investigates and analyses the deorbit performance and mission applicability of the electrodynamic tethered system. To do so, the electrodynamic tethered deorbit dynamics with multi-perturbation is firstly formulated, where the Earth magnetic field, the atmospheric drag, and the Earth oblateness effect are considered. Then, the key system parameters, including payload mass, tether length and tether type, are analyzed by numerical simulations to investigate their influences on the deorbit performance and to give the setting principles for choosing system parameters. Based on this and given an appropriate group of system parameters, numerical simulations are undertaken to study the impact of the mission parameters, including orbit height and orbit inclination, and thus to investigate the mission applicability of the electrodynamic tethered deorbit technology.
