Abstract
Near-pace hypersonic flight has great potential in civil and military use due to its high speed and low cost. To optimize the design and improve the robustness, this paper focuses on the integrated guidance and control (IGC) design with nonlinear actuator dynamics in the terminal phase of hypersonic flight. Firstly, a nonlinear integrated guidance and control model is developed with saturated control surface deflection, and third-order actuator dynamics is considered. Secondly, a neural network is introduced using an extended state observer (ESO) design to estimate the complex model uncertainty, nonlinearity and disturbance. Thirdly, a command-filtered back-stepping controller is designed with flexible designed sliding surfaces to improve the terminal performance. In this process, hybrid command filters are implemented to avoid the influences of disturbances and repetitive derivation, meanwhile solving the problem of unknown control direction caused by nonlinear saturation. The stability of the closed-loop system is proved by the Lyapunov theory, and the controller parameters can be set according to the relevant remarks. Finally, a series of numerical simulations are presented to show the feasibility and validity of the proposed IGC scheme.
Highlights
Since the 1980s, integrated guidance and control (IGC) has been the subject of lots of studies for tactical missiles, space shuttles and hypersonic flight vehicles
In order to improve the closed-loop performance, the modern guidance and control (G&C) design has involved various techniques such as sliding mode control, adaptive control, disturbance rejection control, anti-windup control, etc., because the system dynamics is obviously characterized by strong states coupling, imprecisely known aerodynamics, complex internal uncertainties and external disturbances, especially in hypersonic flight
This work is motivated by (1) integrated guidance and control design, (2) complex uncertainty and disturbance estimate using an improved extended state observer based on neural network, (3) composite command-filtered back-stepping control with nonlinear constraint
Summary
Since the 1980s, integrated guidance and control (IGC) has been the subject of lots of studies for tactical missiles, space shuttles and hypersonic flight vehicles. This work is motivated by (1) integrated guidance and control design, (2) complex uncertainty and disturbance estimate using an improved extended state observer based on neural network, (3) composite command-filtered back-stepping control with nonlinear constraint.
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