Attitude Control Hardware for Operationally Responsive Space Platforms in LEO

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，它们的应用程序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，由于使用反作用轮时的高质量和功率权衡，使用反作用轮受到显着阻碍。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，并在大型商业和情报卫星上得到广泛应用，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（<150 kg）的控制力矩陀螺仪硬件。我们建议设计、开发和设计一个能够提供> 100 mNm扭矩、>200 mNms角动量，同时消耗<7 W功率和< 700 g质量的原型控制力矩陀螺仪（CMG）。这将使航天器灵活机动，并导致地面高价值目标频繁重访以及空间物体跟踪，在相当低的发射成本。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，以扩大小卫星在军事和国防应用中的应用。从长远来看，该项目是建立在MSCI和约克大学的姿态控制系统（ACS）的研究，进一步发展先进的卫星设计先进的硬件。

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.