L1 adaptive control augmentation for a hypersonic glider

Banerjee, Sanchito (2016). L1 adaptive control augmentation for a hypersonic glider PhD Thesis, School of Mechanical and Mining Engineering, The University of Queensland. doi:10.14264/uql.2016.102

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Author Banerjee, Sanchito
Thesis Title L1 adaptive control augmentation for a hypersonic glider
Formatted title
L1 adaptive control augmentation for a hypersonic glider
School, Centre or Institute School of Mechanical and Mining Engineering
Institution The University of Queensland
DOI 10.14264/uql.2016.102
Publication date 2016-02-26
Thesis type PhD Thesis
Supervisor David Mee
Russell Boyce
Michael Kearney
Total pages 243
Total colour pages 68
Total black and white pages 175
Language eng
Subjects 0901 Aerospace Engineering
Formatted abstract
The aim of this research is to investigate control strategies to carry out a pull out of a ballistic trajectory (initially the same as the sub-orbital ballistic HyShot and HIFiRE trajectories) and a pulsed roll angle bank manoeuvre for a hypersonic glider. This study investigates the performance of two different control methodologies in the presence of aerodynamic, gravimetric and actuator uncertainties: pole placement control (PPC) (as the baseline) and L1 adaptive control (to augment the PPC).

Through simulations, it is shown that the PPC carries out the pull up manoeuvre (by tracking the flight path angle, γc) on a scaled Generic Hypersonic Aerodynamics Model Example (GHAME model). Once the pull-up manoeuvre is carried out the lateral/directional PPCs perform satisfactorily in tracking the commanded roll angle, ϕ and maintaining a sideslip angle, β, of zero degrees. The PPCs presented are all Single Input Single Output (SISO) controllers. Pole-zero plots are utilised to highlight the stability properties of the PPC. All the controllers are stable. The differences in the performance and robustness for the various uncertainty cases are highlighted through the tracking error norm and the time delay margin (TDM). The performance of the PPC significantly worsens in the presence of uncertainties. This deterioration is quantified using tracking error norms, error dynamics acceleration and a control surface metric.

L1 adaptive control is employed as a control strategy to augment the PPC as it allows the decoupling of the control and the estimation loop. The L1 control augmentation design is employed for both the longitudinal and the lateral/directional channels in the presence of matched and unmatched uncertainties. A piecewise constant adaptive law (to estimate the uncertainties) is adopted for all the channels. An additional challenge present in this research is that the flight path angle dynamics of the system display non-minimum phase behaviour. The L1 control theory requires the inversion of the system dynamics, which renders the control law, which cancels the unmatched uncertainties, unstable. An inverse DC gain method is presented and tested. Using this modification, the inversion of the system dynamics is avoided. The main step forward that has been taken in this thesis is the extension of the application of L1 theory and its application to a non-minimum phase state feedback Linear Time Varying (LTV) systems. This modified law prevents a reformulation of the control problem, for example computing an alternative representation of the state estimator in the augmented controller in order to have all the uncertainties come in through the matched channel of the system or having a virtual inertial measurement unit (IMU) in order to make the measured values minimum phase. The L1 augmented controller is able to cancel the uncertainties and is able to restore the performance of the controller and bring the system closer to the desired system performance. The improvement provided by the L1 augmented controller is demonstrated using the tracking error norm and the control surface metric. The augmented controller, however, shows a reduction in the robustness parameter, which is the time-delay margin. This result is consistent with that observed in adaptive control as there is a trade-off between performance and robustness.
Keyword Hypersonic glider flight control
Pole placement control
ℒ1 adaptive control
Longitudinal and lateral/directional control
Descent trajectory
Adaptive augmented controller
Nonminimum phase system
Linear time varying system
Full state feedback control
Time-delay margin

Document type: Thesis
Collections: UQ Theses (RHD) - Official
UQ Theses (RHD) - Open Access
 
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Created: Mon, 22 Feb 2016, 16:58:18 EST by Sanchito Banerjee on behalf of Learning and Research Services (UQ Library)