Robust Tracking Control Design for Spacecraft Under Control Input Saturation

By J. Boskovic, Sai-Ming Li, Raman K. Mehra. 2004

280 citations recorded by the source corpus.

Subfields: Aerospace Engineering, Control and Systems Engineering

View Paper: https://www.semanticscholar.org/paper/f8a85fffc8f8aad028b0a1840723cc1c0ebe3a77

How researchers see this paper

The researchers whose trusted networks rank it highest, strongest advocate first. Every researcher gets a different order.

In Aerospace Engineering

1. Yuanqing Xia
2. Qinglei Hu
3. Zhenglong Zhu
4. M. Fu
5. Youmin Zhang
6. Bing Xiao
7. Xu Jin
8. Kunfeng Lu

In Control and Systems Engineering

1. Yuanqing Xia
2. M. Fu
3. Zhenglong Zhu
4. Qinglei Hu
5. Bing Xiao
6. Youmin Zhang
7. Xing Huo
8. Huijun Gao

Citations in the corpus

• Fault-Tolerant Tracking Control of Spacecraft with Attitude-Only Measurement Under Actuator Failures (2014, background): “Analysis and design of attitude systems with actuator saturation were studied in [40–45].”
• Adaptive Sliding Mode Fault Tolerant Attitude Tracking Control for Flexible Spacecraft Under Actuator Saturation (2012, unknown): “[18], Panagiotis et al.”
• Inverse optimal adaptive control for attitude tracking of spacecraft (2005, background): “The equations that govern attitude maneuvers and attitude tracking are nonlinear and coupled, thus, the attitude control system must consider these nonlinear dynamics.”
• Robust adaptive sliding mode attitude maneuvering and vibration damping of three-axis-stabilized flexible spacecraft with actuator saturation limits (2009, background): “Extensive results pertaining to spacecraft attitude control systems containing actuator saturation nonlinearities have been presented by Boskovi´ Li, and Mehra [8, 9 ], Tsiotras and Luo [17], Robinett et al. [18], Wallsgrove and Akella [19]; Yakoubi and Chitour [20], Xu and Lam [21], and Grimm et a”
• Adaptive Sliding Mode Control for Attitude Stabilization With Actuator Saturation (2011, background): “In [14] and [15], the research work gives a control design based on the assumption that the external disturbance is bounded by a known upper bound.”
• Indirect Robust Adaptive Fault -Tolerant Control for Attitude Tracking of Spacecraft (2008, background): “taken from [13,14,22] (J0 is usually nondiagonal unless the axis of the body frame and the principal axis coincide).”