Zhang Kangyu, Lu Kuan, Gu Xiaohui, Fu Chao, Zhao Shibo
Institute of Vibration Engineering, Northwestern Polytechnical University, Xi'an 710072, China.
State Key Laboratory Mechanical Behavior and System Safety of Traffic Engineering Structures, Shijiazhuang Tiedao University, Shijiazhuang 050043, China.
Sensors (Basel). 2021 Dec 23;22(1):62. doi: 10.3390/s22010062.
In recent years, Tethered Space Systems (TSSs) have received significant attention in aerospace research as a result of their significant advantages: dexterousness, long life cycles and fuel-less engines. However, configurational conversion processes of tethered satellite formation systems in a complex space environment are essentially unstable. Due to their structural peculiarities and the special environment in outer space, TSS vibrations are easily produced. These types of vibrations are extremely harmful to spacecraft. Hence, the nonlinear dynamic behavior of systems based on a simplified rigid-rod tether model is analyzed in this paper. Two stability control laws for tether release rate and tether tension are proposed in order to control tether length variation. In addition, periodic stability of time-varying control systems after deployment is analyzed by using Floquet theory, and small parameter domains of systems in asymptotically stable states are obtained. Numerical simulations show that proposed tether tension controls can suppress in-plane and out-of-plane librations of rigid tethered satellites, while spacecraft and tether stability control goals can be achieved. Most importantly, this paper provides tether release rate and tether tension control laws for suppressing wide-ranging TSS vibrations that are valuable for improving TSS attitude control accuracy and performance, specifically for TSSs that are operating in low-eccentricity orbits.
近年来，系链空间系统（TSSs）因其显著优势：灵活性、长生命周期和无燃料发动机，在航空航天研究中受到了广泛关注。然而，在复杂空间环境中，系链卫星编队系统的构型转换过程本质上是不稳定的。由于其结构特性和外层空间的特殊环境，TSSs容易产生振动。这类振动对航天器极为有害。因此，本文基于简化的刚性杆系链模型分析了系统的非线性动力学行为。为了控制系链长度变化，提出了两种系链释放速率和系链张力的稳定性控制律。此外，利用弗洛凯理论分析了展开后时变控制系统的周期稳定性，并得到了系统渐近稳定状态下的小参数域。数值模拟表明，所提出的系链张力控制能够抑制刚性系链卫星的面内和平动，同时可以实现航天器和系链的稳定性控制目标。最重要的是，本文提供了系链释放速率和系链张力控制律，用于抑制大范围的TSSs振动，这对于提高TSSs姿态控制精度和性能具有重要价值，特别是对于在低偏心率轨道运行的TSSs。
