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本文介绍一种基于控制力矩陀螺(CMG)的新型姿态控制系统。CMG可以在不增加功耗、质量和体积的条件下为小卫星提供独特的控制力矩、角动量和姿态机动能力,这将有助于小卫星变得更加机动灵活。灵活性可以显著地扩大航天器的应用范围,提高航天器的效能并且可以大大增加地球观测和科学任务的数据返回率。在接下来的章节中介绍CMG的基本特性,分析了一种为增强型微小卫星设计的低成本、小型化单框架控制力矩陀螺(SGCMG)方案。文中建议的一个SGCMG参数表明,使用CMG有许多优点。该SGCMG能够产生9.82mNm的控制力矩,并且已经通过了气浮台试验验证。对SGCMG和反作用轮(RW)的对比证明,使用SGCMG可以降低整星的重量和功耗。
This article introduces a new type of attitude control system based on the control moment gyroscope (CMG). CMGs provide unique control torques, angular momentum and attitude maneuvering capabilities for small satellites without increasing power, mass and volume, which will help make small satellites more maneuverable. Flexibility can significantly expand the spacecraft’s applications, enhance the effectiveness of spacecraft and greatly increase data return rates for Earth observation and scientific missions. In the following sections, we introduce the basic features of CMG and analyze a low-cost, miniaturized single-frame control moment gyro (SGCMG) scheme designed for enhanced micro-satellites. The proposed SGCMG parameter suggests that there are many advantages to using CMG. The SGCMG is capable of producing 9.82mNm of control torque and has passed the flotation bench test. A comparison of the SGCMG with the reaction wheel (RW) proves that the use of SGCMG can reduce the overall weight and power consumption.