Development of a Variable Inertia Reaction Wheel System for Spacecraft Attitude Control
Development of a Variable Inertia Reaction Wheel System for Spacecraft Attitude Control
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用于航天器姿态控制的变惯量反作用轮系统的开发
DOI：
10.2514/6.2004-5132
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发表时间：
2004
期刊：
影响因子：
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通讯作者：
Eric N. Johnson
中科院分区：
文献类型：
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作者：
John A. Christian;Michael Turbe;Erik M. Kabo;Laura C. Manno;Eric N. Johnson
姿态控制是大多数航天器的重要基本功能。本实验的主要目的是通过引入变惯量反作用轮来提高反作用轮姿态控制系统的性能和灵活性。这种增强可能提供至少两个优点：可变精度和车辆重新定向而不改变反作用轮角速度。为了证明这些优点，在美国航天局KC-135 A“失重奇迹V”号飞机上，在微重力环境中飞行了一个可变惯性反作用轮系统的原型，作为自由浮动实验。在飞行过程中收集的数据表明，控制系统表现良好，可变惯性系统提供了更大的灵活性，在姿态控制。
*† * * ‡ Attitude control is an important basic function for most spacecraft. The primary objective of this experiment was to improve the capability and flexibility of a reaction wheel attitude control system by introducing variable inertia reaction wheels. This enhancement might provide at least two advantages: variable precision and vehicle reorientation without changing the reaction wheel angular velocity. To demonstrate these advantages, a prototype of a variable inertia reaction wheel system was flown in a microgravity environment aboard NASA’s KC-135A “Weightless Wonder V” aircraft as a free floating experiment. The data collected during flight suggests the control system performed well, and that a variable inertia system offers increased flexibility in attitude control.