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Modeling of Orbital and Attitude Dynamics of Nanosatellites Controlled via Active Electrostatic Charging

机译:通过主动静电充电控制纳米替肽的轨道和姿态动态的建模

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The large-scale exploration of airless bodies, such as asteroids and moons, is gaining interest, however it is limited by mobility issues: the lack of atmosphere, low gravity, and unknown soil properties pose difficult challenges for many forms of traditional locomotion. The environment in proximity of these bodies is also electrically charged due to interactions with solar wind and UV radiation. The EGlider (Electrostatic Glider) concept would be able to overcome these mobility issues by leveraging the natural environment, allowing operations in close proximity of the surface, while enabling long duration missions by minimizing propellant consumption. The EGlider is an advanced concept for small satellite mobility and propulsion, which relies on the electric fields naturally present around airless bodies in order to generate forces and torques useful for maneuvering. It does so by extending electrically charged appendages, which enable it to electrostatically soar above the surface. By differentially charging its electrodes it can also produce torques to control its attitude. The charges are maintained by continuous active ion or electron emission from the spacecraft, in order to cancel out the neutralizing influx of charges from surrounding plasma. An investigation of the spacecraft-plasma interaction was carried out. This included studying the effect of electrode geometry and calculating the charge-to-mass ratios required to enable several mission scenarios. Long, thin wire electrodes were identified to be the most power-efficient and would allow power-to-weight ratios achievable with current nanosatellite technologies. High electrode potential represents the main limiting factor for the system design. In order to test the feasibility of active control by means of differential charging, a simple 2D interaction model was developed, and a feedback controller to stabilize the vehicle was tested in a simulation environment. The results confirmed that good performance
机译:对无气体的大规模探索,例如小行星和卫星,正在获得兴趣,但它受到迁移性问题的限制:缺乏大气,低重力和未知的土壤性质对多种形式的传统运动构成困难挑战。由于与太阳风和紫外线辐射的相互作用,这些体接近的环境也是电荷的。 EGLIDER(静电滑翔机)概念将能够通过利用自然环境来克服这些移动性问题,允许在表面附近的操作,同时通过最小化推进剂消耗来实现长时间任务。 EGLIDER是小卫星移动和推进的先进概念,它依赖于自然存在于无气体周围的电场,以产生可用于操纵的力和扭矩。它通过延伸电荷的附属物来实现,使其使其能够在表面上静电。通过差异地充电,它还可以产生扭矩来控制其姿态。通过来自航天器的连续活性离子或电子发射来维持电荷,以取消周围等离子体的充电的中和涌入。进行了对航天器 - 血浆相互作用的研究。这包括研究电极几何形状的效果并计算能够实现若干任务方案所需的充电量比。长时间,薄薄的线电极被识别为最有效的,并且可以利用当前纳米卫星技术实现能量的重量比率。高电极电位代表了系统设计的主要限制因素。为了通过差分充电测试主动控制的可行性,开发了一种简单的2D交互模型,并在仿真环境中测试了稳定车辆的反馈控制器。结果证实表现良好

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