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首页> 外文期刊>Journal of aerospace engineering >Design, Manufacturing, and Ground Testing of a Control-Moment Gyro for Agile Microsatellites
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Design, Manufacturing, and Ground Testing of a Control-Moment Gyro for Agile Microsatellites

机译：敏捷微卫星控制力矩陀螺的设计，制造和地面测试

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A recently emerged driving requirement for microsatellites is a precise and fast attitude maneuvering capability. Agility enhances the operational efficiency of missions requiring a high level of retargeting ability, such as space station and satellite on-orbit servicing, formation flying, Earth monitoring, and space-based space debris observation and tracking. Three-axis stabilized microsatellites are mainly equipped with momentum wheels, barely meeting agility requirements. In this paper, the design and manufacturing of a cluster of four single-gimbal variable-speed control-moment gyros (SGCMGs), suitable for attitude control with high-agility capability of a 10-30 kg class micro-satellite, is presented. The flywheel design is based on a brushless motor out-runner configuration, in which the motor magnets, embedded in the rotor, provide for the wheel inertia. This configuration has the advantage of providing a high inertia while minimizing cogging torque at low speed. The elimination of the wheel dummy mass provides a significant improvement in the system mass efficiency. In addition, this configuration allows using commercial off-the-shelf parts, eliminating the wheel-balancing procedure with evident jitter limitation and economic and development time benefits. A relevant feature is the electronics architecture based on a field-programmable gate array (FPGA) integrated circuit, chosen to improve power efficiency and provide a high level of reliability for the system. This can be assured by proper time and space redundancy for each low-level logic block of the design. The system performance in terms of provided torque and power consumption has been experimentally measured by using a ground-testing prototype mounted on a test bed, and the results are reported. The results confirm the effectiveness of the proposed actuator as an efficient solution for the attitude control of microsatellites, in terms of mass, volume, and power constraints. (C) 2017 American Society of Civil Engineers.
机译：最近出现的对微卫星的驾驶要求是精确和快速的姿态操纵能力。敏捷性提高了需要高水平重新定向能力的任务的运营效率，例如空间站和卫星在轨维修，编队飞行，地球监测以及天基空间碎片观察和跟踪。三轴稳定微卫星主要配备动量轮，几乎不能满足敏捷性要求。本文提出了一种适合于姿态控制且具有敏捷性的10-30 kg级微卫星的，由四个单臂变速控制力矩陀螺（SGCMG）组成的集群的设计和制造。飞轮设计基于无刷电机外转子配置，其中嵌入转子中的电机磁铁可提供车轮惯性。该构造的优点是提供高惯性，同时最小化低速下的齿槽转矩。车轮伪质量的消除大大提高了系统质量效率。此外，这种配置允许使用现成的商用零件，从而消除了车轮平衡过程，并具有明显的抖动限制以及经济和开发时间上的好处。一个相关的功能是基于现场可编程门阵列（FPGA）集成电路的电子体系结构，该体系结构旨在提高电源效率并为系统提供高水平的可靠性。通过为设计的每个低级逻辑块提供适当的时间和空间冗余，可以确保这一点。通过使用安装在测试台上的地面测试原型，已通过实验测量了系统在提供的扭矩和功耗方面的性能，并报告了结果。结果证实了所提出的执行器作为质量，体积和功率约束方面的微卫星姿态控制的有效解决方案的有效性。 （C）2017年美国土木工程师学会。

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    《Journal of aerospace engineering》 |2017年第5期|04017039.1-04017039.9|共9页
  • 作者

    Arena Lorenzo; Piergentili Fabrizio; Santoni Fabio;

  • 作者单位

    Univ Roma La Sapienza, DIMA, Via Eudossiana 18, I-00184 Rome, Italy;

    Univ Roma La Sapienza, DIMA, Via Eudossiana 18, I-00184 Rome, Italy;

    Univ Roma La Sapienza, DIAEE, Via Eudossiana 18, I-00184 Rome, Italy;

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