Abstract
A novel integrated guidance and control (IGC) scheme for a Re-entry Hypersonic Vehicle (RHV) is proposed with the capabilities of online aerodynamic coefficient estimation based on an Unscented Kalman Filter and online trajectory generation based on the Gaussian pseudospectral method. A linear quadratic regulator is adopted for trajectory tracking guidance and a second-layer sliding mode controller is designed for attitude control. The variation of lift and drag coefficients are modeled and estimated online, based on which a new trajectory can be generated. The commands of trajectory generation are set as moments of actuators and their extremums pose more constraints on the rate and acceleration of flow angles. Comprehensive simulations are conducted and comparable IGC performances with normal conditions are obtained under large aerodynamic coefficient errors according to online generated trajectory, which proves the effectiveness and advantages of the proposed IGC scheme.
Highlights
When a re-entry hypersonic vehicle is launched, it reaches a specific altitude and re-enters the atmosphere from near-Earth orbit
Compared with other known re-entry integrated guidance and control (IGC) schemes, the following contributions are made by our research from a scientific view: (1) Constraints of the rate and acceleration of flow angles are considered in trajectory generation based on the Gauss pseudospectral method (GPM). (2) Dynamic models with 6 degrees of freedom (DOFs) are applied in the guidance laws of Linear Quadratic Regulator (LQR), which takes the Re-entry Hypersonic Vehicle (RHV)’s control constraints into account and can provide expected flow angles and their rates for attitude control system
In order to improve the guidance and control performance, a novel IGC scheme is proposed with the capabilities of online aerodynamic coefficient estimation based on a Unscented Kalman Filter (UKF) and online trajectory generation based on the GPM
Summary
When a re-entry hypersonic vehicle is launched, it reaches a specific altitude and re-enters the atmosphere from near-Earth orbit. Online trajectory generation is required for a changing target scenario; online aerodynamic coefficient estimation is meaningful in terms of improving the IGC performance under obvious disturbances and uncertainty. A novel IGC scheme for RHV is proposed with the capabilities of online aerodynamic coefficient estimation based on UKF and online trajectory generation based on the GPM. Compared with other known re-entry IGC schemes, the following contributions are made by our research from a scientific view: (1) Constraints of the rate and acceleration of flow angles are considered in trajectory generation based on the GPM. (3) During guidance lift and drag, coefficients of RHV are estimated online for re-entry vehicles through UKF for robust IGC and possible online trajectory construction.
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