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: 2018
• 资助国家: 加拿大
• 起止时间: 2018-01-01 至 2019-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=657059
• 关键词: Attitude; Control; Hardware; Operationally; Responsive

Small Satellites (or Smallsats, in short) are increasingly recognized for their versatility and efficienty. In**particular, their applications are now found for data collection that could directly benefit both the Operationally**Responsive 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 satellites**while using reaction wheels is significantly hampered by the high mass and power trade-off when using**reaction wheels. Control Moment Gyroscope is the unique alternative actuation mechanism that provides the**hosting satellite the increased agility while requiring less power and mass compared to reaction wheels which**is invaluable in a smallsat application. Despite this crucial advantage and its wide usage in larger commercial**and intelligence satellites, there is no proper Control Moment Gyroscope available in the market for this class**of small satellites.**The proposed research is to develop a Control Moment Gyroscope hardware suitable for the microsatellite**class of satellites (<150 kg). We propose to design, develop and engineer a prototype control moment**gyroscope (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 high**value 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 civilian**and military applications by developing a highly accurate, agile control actuator. In long run, the project is to**build on MSCI and York University's Attitude Control System (ACS) research to further develop advanced**attitude hardware for advanced satellite design.

小型卫星（或简称Smallsats）因其多功能性和高效性而日益受到认可。特别是，它们的应用现在被发现用于数据收集，可以直接有利于操作响应空间（ORS）的情报目标以及商业部门的高收入野心。目前，** 所有的小型卫星都依靠反作用轮来实现三轴控制，并提高小型卫星的敏捷性 **，而使用反作用轮时，由于使用反作用轮时的高质量和功率权衡而受到严重阻碍。控制力矩陀螺仪是一种独特的替代驱动机制，它为 ** 托管卫星提供了更高的敏捷性，同时与反作用轮相比，它需要更少的功率和质量，这在小卫星应用中是非常宝贵的。尽管有这一关键的优势，而且在大型商业卫星和情报卫星中得到广泛应用，但市场上还没有适合这类小型卫星的控制力矩陀螺仪。拟议的研究是开发一种适用于微型卫星 ** 级卫星（<150公斤）的控制力矩陀螺仪硬件。我们建议设计、开发和设计一个原型控制力矩 ** 陀螺仪（CMG），该陀螺仪能够提供> 100 mNm的扭矩、>200 mNms的角动量，同时消耗 **<7 W的功率和< 700 g的质量。这将使航天器能够灵活机动，并导致地面高 ** 价值目标的频繁重访以及空间物体的跟踪，而发射成本却大大降低。该项目旨在提供创新的空间产品，通过开发一种高精度、灵活的控制致动器，扩大小型卫星在民用和军用领域的应用。从长远来看，该项目将在MSCI和约克大学的姿态控制系统（ACS）研究的基础上，进一步开发先进的姿态硬件，用于先进的卫星设计。