Dr Pyare Mohan Tiwari

2008-2015
Current Position: Asst Professor, Amity University, Noida.

Attitude control system (ACS) plays a significant role in the success of a space mission. The attitude accuracy, convergence time to the desired attitude, robustness against the inertia uncertainty and external disturbances, and required control input to accomplish the target attitude are the performance criteria to evaluate the ACS efficacy. Sliding mode control, a robust control method, has been investigated greatly for the attitude control of a spacecraft. However, chattering and asymptotic convergence are the limitations for this method. In last two decades, the sliding mode control concept has been equipped with new techniques like terminal sliding mode control, integral sliding mode control, and higher order sliding mode control. These techniques are more efficient compared to the standard sliding mode control. The objective of this thesis is to present efficient three-axes control methods for the attitude control of a rigid spacecraft. The attitude control method should ensure the high attitude accuracy, the fast convergence speed, the robustness against uncertainty and disturbances, and the limited control energy use. To represent the attitude, an efficient attitude parameter of quaternion is adopted. To achieve the control objectives, advanced techniques of sliding mode control are applied. The first contribution is the design of a finite time convergent continuous time attitude controller. In this approach, a new fast terminal sliding surface is proposed and the control law is derived. In the next contribution, a non-singular fast terminal sliding surface is proposed and then equivalent control and a reaching law control are comprised to present a finite time fast converging attitude control law. Then, adaptive gain based attitude control law is proposed. The presented control law is operating on a non-singular fast terminal sliding surface and adaptive laws are proposed to eliminate the need for upper bound of uncertainty and external disturbances. Furthermore, higher-order sliding mode based attitude control methods are developed to eliminate chattering without demeaning robustness. The first contribution is a second-order sliding mode based attitude controller. In control design, first a linear sliding surface is selected and then a second-order sliding mode control law is formulated in fast terminal sliding mode. Further, attitude control laws are presented applying higher order sliding mode control in integral sliding mode and global robustness is guaranteed.

Publications

Journals

• Pyare Mohan Tiwari, S. Janardhanan and Mashuq-un-Nabi, "Spacecraft Attitude Control using Non-singular Finite Time Convergence Fast Terminal Sliding Mode", International Journal of Instrumentation Technology, Vol. 1, No. 2, pp. 124-142, 2012 doi : 10.1504/IJIT.2012.053289.


• Pyare Mohan Tiwari, S. Janardhanan and Mashuq-un-Nabi, "Rigid Spacecraft Attitude Control using Adaptive Non-singular Fast Terminal Sliding Mode", Journal of Control, Automation and Electrical Sciences, Vol. 26, No. 2, pp. 115--124, Jan, 2015. (doi : 10.1007/s40313-014-0164-0).


• Pyare Mohan Tiwari, S. Janardhanan and Mashuq-un-Nabi, "Rigid spacecraft attitude control using adaptive integral second order sliding mode", Aerospace Science and Technology, Vol. 42, pp. 50-57, Apr-May 2015 (doi : 10.1016/j.ast.2014.11.017).

Conferences

• S. Janardhanan, M. Nabi and P. M. Tiwari, "Attitude Control of Magnetic Actuated Spacecraft using Super-Twisting Algorithm with Nonlinear Sliding Surface", 12th International Workshop on Variable Structure Systems (VSS2012), pp. 46--51, IIT Bombay, India, Jan. 2012.


• Pyare Mohan Tiwari, S. Janardhanan and Mashuq un Nabi, "Rigid Spacecraft Attitude Tracking using Finite Time Sliding Mode Control", Proc. Third International Conference on Advances in Control and Optimization of Dynamical Systems (ACODS-2014), pp. 263-270, India, Mar. 2014. doi : 10.3182/20140313-3-IN-3024.00168.


• P. M. Tiwari, S. Janardhanan & M. Nabi, "A Finite Time Convergent Continuous Time Sliding mode Controller for Spacecraft Attitude Control", 11th International Workshop on Variable Structure Systems, Mexico City, Mexico, 26-28 June 2010 .

Book Chapter

• Pyare Mohan Tiwari, S. Janardhanan and Mashuq un Nabi, "Rigid Spacecraft Fault-Tolerant Control using Adaptive Fast Terminal Sliding Mode", in Advances and Applications in Sliding Mode Control Systems, Eds. Ahmad Taher and Quan Min Zhu, Studies in Computational Intelligence, Vol. 576, pp. 381-406, Springer, 2015. DOI : 10.1007/978-3-319-11173-5_14. .