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Design and analysis of nano momentum wheel for picosatellite attitude control system

机译:微卫星姿态控制系统的纳米动量轮设计与分析

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Purpose - Recent advances in nano and picosatellite missions and future such missions require faster and accurate pointing accuracies using reaction wheels for attitude control purposes. The ability to put one or three reaction wheels on the spacecraft in the 1-20 kg range enables new classes of missions. The purpose of this paper is to present the detailed design, analysis, and construction of a miniature reaction wheel prototype. The designed pico-reaction wheel promises to fulfill the need for low cost, low mass, low power, high reliability, and high-accuracy attitude control systems for applications such as communications, remote sensing, and space science. Design/methodology/approach - Details about the design, analysis and development of pico-reaction wheel are discussed. The development status of the system is outlined and the working prototype of the device is described and some preliminary test results are given. Requirements specifications, design and analysis and finite element analysis are covered. Findings - A fully functional prototype has been developed and testing has been conducted that demonstrated the effectiveness of the device. The pico-reaction wheel offers a new attitude control system implementation strategy for pico and nanosatellite missions that can help to significantly reduce the spacecraft costs. The key to our success has been to design the reaction wheel from ground-up for simplicity. Originality/value - The designed pico-reaction wheel satisfied all the constraints and requirements. Furthermore, its advantages include scalability and modularity by virtue of using commercial-off-the-shelf components. A pico-reaction wheel has been successfully designed and is now available to pico and nanosatellite builders at a cost that is consistent with low-cost research missions.
机译:目的-纳米和微卫星任务的最新进展以及未来的此类任务要求使用反作用轮进行姿态控制,以实现更快,更准确的指向精度。在飞船上放置1或3公斤反作用轮的能力可实现新型任务。本文的目的是介绍微型反作用轮原型的详细设计,分析和构造。设计的微动反应轮有望满足通信,遥感和太空科学等应用对低成本,低质量,低功率,高可靠性和高精度姿态控制系统的需求。设计/方法/方法-讨论了有关微反作用轮的设计,分析和开发的详细信息。概述了系统的发展状况,描述了该设备的工作原型,并给出了一些初步的测试结果。涵盖了需求规格,设计和分析以及有限元分析。发现-已开发出功能齐全的原型,并进行了测试,证明了该设备的有效性。微微反应轮为微微和纳米卫星任务提供了一种新的姿态控制系统实施策略,可以帮助显着降低航天器成本。我们成功的关键在于从根本上设计反作用轮以简化操作。独创性/价值-设计的微微反应轮满足所有约束和要求。此外,它的优点包括通过使用现成的商用组件来实现可伸缩性和模块化。微型反应轮已经成功设计,现在可以以与低成本研究任务一致的价格提供给微型和纳米卫星制造商。

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