Finite time suboptimal control design of nonlinear systems with θ-D technique and implementation to aerospace applications

“A finite time suboptimal control strategy (named θ - D approximated algorithm) was proposed in this study, which can provide the control engineers with a novel effective and efficient design tool from the finite time optimal perspective. Based on the framework of this proposed method, the original nonlinear dynamics were formulated in pseudo-linear form, and the performance index was denoted by a linear quadratic regulator prototype in this research. After that, the approximated solutions to intractable Hamilton-Jacobi-Bellman (HJB) equation were acquired by putting vanishing perturbation terms into the performance index. By tuning the parameters in perturbation terms, semi-global stability and sub-optimalilty was guaranteed. By taking the advantages of the perturbation terms, the large control was not required to cope with the large deviation at the initial time, which alleviates the severe tests of the actuators. The detailed procedure to develop this technique and corresponding stability proof were provided. The effectiveness of the proposed technique was verified by solving the two-dimensional benchmark problem, and the other three aerospace applications, including Reusable Launch Vehicle (RLV) landing problem, multiple satellites docking problem, and satellite maneuvering considering J₂ perturbation problem. In this research, contrary to the finite-time state dependent Riccati equation (FSDRE) technique , the proposed technique did not need excessive online computation, which makes the real-time implementation in various engineering scenarios possible since the computational resources are always limited for any specific engineering application; thus, leading to the major contribution of this research for avoiding the online computation of nonlinear Riccati equation and matrix inverse operation at each sample time”--Abstract, page iii.

Name thesis:degree_name

Ph. D. in Mechanical Engineering

Grantor

Missouri University of Science and Technology

Author dc:creator

• Yao, Jie

• Aerospace Engineering
• Mechanical Engineering

Repository record dc:identifier

https://scholarsmine.mst.edu/doctoral_dissertations/3118

OAI identifier oai:identifier

oai:scholarsmine.mst.edu:doctoral_dissertations-4123