Attitude Control Hardware for Operationally Responsive Space Platforms in LEO

用于低地球运行响应空间平台的姿态控制硬件

• 批准号: 522903-2017
• 负责人: Lee, Regina
• 金额: $ 6.41万
• 依托单位: York University
• 依托单位国家: 加拿大
• 项目类别: Collaborative Research and Development Grants
• 财政年份: 2019
• 资助国家: 加拿大
• 起止时间: 2019-01-01 至 2020-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=692357
• 关键词: Attitude; Control; Hardware; Operationally; Responsive

Small Satellites (or Smallsats, in short) are increasingly recognized for their versatility and efficienty. Inparticular, their applications are now found for data collection that could directly benefit both the OperationallyResponsive Space (ORS) intelligence goals as well as commercial sector's high revenue ambitions. Currently,all small satellites rely on reaction wheels to achieve 3-axis control and increasing the agility of small satelliteswhile using reaction wheels is significantly hampered by the high mass and power trade-off when usingreaction wheels. Control Moment Gyroscope is the unique alternative actuation mechanism that provides thehosting satellite the increased agility while requiring less power and mass compared to reaction wheels whichis invaluable in a smallsat application. Despite this crucial advantage and its wide usage in larger commercialand intelligence satellites, there is no proper Control Moment Gyroscope available in the market for this classof small satellites.The proposed research is to develop a Control Moment Gyroscope hardware suitable for the microsatelliteclass of satellites (<150 kg). We propose to design, develop and engineer a prototype control momentgyroscope (CMG) capable of providing > 100 mNm torque, >200 mNms angular momentum, while consuming<7 W power and mass < 700 grams. This will allow spacecraft agile maneuvering and result in ground highvalue target frequent revisits as well as space object tracking, within considerably lower launch cost.The project aims to provide innovative space product to broaden applications of small satellites in both civilianand military applications by developing a highly accurate, agile control actuator. In long run, the project is tobuild on MSCI and York University's Attitude Control System (ACS) research to further develop advancedattitude hardware for advanced satellite design.

小型卫星（简称Smallsats）因其多功能性和高效性而日益受到人们的认可。特别是，它们的应用现在被发现用于数据收集，可以直接有利于运营响应空间（ORS）情报目标以及商业部门的高收入目标。目前，所有的小卫星都依靠反作用轮来实现三轴控制，提高小卫星的敏捷性，而使用反作用轮时，高质量和功率权衡明显阻碍了使用反作用轮。控制力矩陀螺仪是独特的替代驱动机制，提供托管卫星增加的灵活性，同时需要更少的功率和质量相比，这在小型卫星应用中是无价的反作用轮。尽管这一关键优势及其在大型商业和智能卫星中的广泛使用，但在这类小型卫星的市场上没有适当的控制力矩陀螺仪。本课题的研究目标是开发一种适用于微卫星级（小于150kg）卫星的控制力矩陀螺仪硬件。我们建议设计、开发和制造一个原型控制力矩陀螺仪（CMG），该陀螺仪能够提供>00毫微米的扭矩，>200毫微米的角动量，而功耗小于7瓦，质量小于700克。这将允许航天器灵活机动，并导致地面高价值目标频繁重访以及空间目标跟踪，在相当低的发射成本内。该项目旨在通过开发高精度、敏捷控制执行器，提供创新空间产品，以扩大小型卫星在民用和军事应用中的应用。从长远来看，该项目将建立在MSCI和约克大学姿态控制系统（ACS）研究的基础上，进一步开发先进卫星设计的先进姿态硬件。