Attitude Control Hardware for Operationally Responsive Space Platforms in LEO

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，可以直接受益于操作响应空间（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，由于质量和功率的权衡，使用反作用轮明显受到阻碍。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，反作用轮**是一个非常宝贵的小卫星应用程序。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，但市场上没有适当的控制力矩陀螺仪可用于此类小型卫星。**提出的研究是开发一种适用于微卫星**级卫星（< 150kg）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<7瓦，质量< 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，该项目将以MSCI和约克大学的姿态控制系统（ACS）研究为基础，进一步开发先进的姿态硬件，用于先进的卫星设计。

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.