Minimum Acceleration Guidance Law for Spaceplane in Ascent Phase via Exact Linearization

Abstract

A new guidance and control system for a spaceplane is presented. The dynamics of the spaceplane has strong nonlinearity, due to which it is difficult to determine the optimal trajectory analytically and to design a stable trajectory tracking system. Therefore, in this study, we attempt to design a guidance and control system using a state-space exact linearization method without any approximation. Then, a minimum acceleration guidance law is derived analytically by solving a two-point boundary-value problem. Lastly, a trajectory control system is designed to track the vehicle with respect to the reference trajectory generated by the guidance system. The numerical simulation results confirm the validity of the linearized model, the optimality of the guidance system and the good tracking property of the developed system.

Constrained Adaptive Backstepping Control for Re-entry Vehicle

“…Flatness represents the characteristics of a nonlinear system using a structure similar to that of a linear system. [2][3][4] In the exact linearization method, nonlinear mapping transforms an original system into a system suitable for the application of feedback linearization. 7,8) In this study, the extended method is introduced to obtain the online trajectory generation algorithm analytically.…”

“…[2][3][4] For the study of the guidance and control system using a concept of flatness, Morio et al proposed a trajectory tracking control system for offline trajectories. 5,6) In the online trajectory generation system proposed in this paper, the trajectory is generated on the basis of a performance index that minimizes the body acceleration to suppress the load factor and dynamic pressure.…”