Hypersonic glider control using higher order sliding mode control

Tournes, Christian; Hanks, Gerald E.

doi:10.1109/secon.2008.4494302

Cited by 7 publications

(17 citation statements)

References 18 publications

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“…Compared with the studies in the control of powered HSVs, limited research is available on the development of controllers for unpowered HSVs [10,16,19,[47][48][49][50][51]. Consequently, this distinct focus on developing control methodologies for powered HSV leaves a large gap in the literature relating to development of control systems for unpowered HSVs once the SCRAMJET has been fired and tested.…”

Section: Background To the Researchmentioning

confidence: 99%

“…Over the past few decades, research into the control of HSVs, especially hypersonic gliders, has become a distinctive part of research into the control of re-entry vehicles [10,19,[47][48][49][50][51]102]. Initial studies mainly focused on the static stability of hypersonic gliders [19] followed by studies of control along a re-entry trajectory of the shuttle [58,103,104].…”

Section: Complications With Hypersonic Control and Modellingmentioning

confidence: 99%

“…Methods such as extended command governor (ECG) and sliding mode control have been employed to control the trajectory of gliders [48,51]. More recently, pole placement control (PPC) and adaptive control has been used to control hypersonic vehicles along a glide trajectory [10,16].…”

Section: Trajectory Control Of Hypersonic Glidersmentioning

confidence: 99%

“…The study into unpowered hypersonic gliders has attracted the use of both linear and nonlinear control methodologies [10,19,47,48,51]. This research work also uses the baseline controller, which is a linear controller, and the augmentation of the baseline controller is through a nonlinear adaptive controller.…”

Section: Introductionmentioning

confidence: 99%

“…As an alternative, nonlinear adaptive controllers have been employed in the HSV configuration domain [10,16,22,33,[37][38][39][40][41][42][43]. In the research positioning matrix of Fig 1.3, quadrants A and B represent the studies undertaken for linear and nonlinear control methodologies to stabilise powered HSV.Thus, while in the area of control research a large body of scholarly work exists, the extent of research is directed at linear and nonlinear control of powered vehicles [1,30,[44][45][46].Compared with the studies in the control of powered HSVs, limited research is available on the development of controllers for unpowered HSVs [10,16,19,[47][48][49][50][51]. Consequently, this distinct focus on developing control methodologies for powered HSV leaves a large gap in the literature relating to development of control systems for unpowered HSVs once the SCRAMJET has been fired and tested.…”

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L1 adaptive control augmentation for a hypersonic glider

Banerjee¹

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ii ABSTRACTThe 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 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, ) 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, and maintaining a sideslip angle, , of zero degrees. The PPCs presented are all SingleInput 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.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 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 control theory requires the inversion of the system dynamics, which renders the control law, which cancels the unmatched uncertainties, unstable. An inverse ABSTRACT iii 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 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 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 augmented controller is d...

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Section: Background To the Researchmentioning

confidence: 99%

Section: Complications With Hypersonic Control and Modellingmentioning

confidence: 99%

Section: Trajectory Control Of Hypersonic Glidersmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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L1 adaptive control augmentation for a hypersonic glider

Banerjee¹

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An improved decentralized control method for Bank‐to‐Turn missile autopilot design

Qin

Duan

2011

Asian Journal of Control

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In this paper, an improved decentralized control method is proposed to design a bank-to-turn (BTT) missile autopilot. Compared to the general diagonal blocked Lyapunov function method, the improved decentralized control method by considering the coupling terms as the structured uncertainty can provide a simpler design, tolerate more types of uncertainties and yield a better dynamic performance. Moreover, this method can be extended to multimodel systems expediently. Due to the structural constraints, the decentralized controller may not realize the tracking control target under some conditions, and this paper also provides such a condition. The decentralized controller design is formulated in terms of linear matrix inequality (LMI) optimization, and the simulation results demonstrate the effectiveness of the proposed method.

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Hybrid high-order sliding mode-based control for multivariable cross-coupling systems: Scale-laboratory helicopter system application

2017

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This paper presents a high-order sliding mode approach to design variable structure controllers for nonlinear multivariable cross-coupling systems whereby a change in either control input affects the control loops of all the subsystems dynamics. A hybrid-sliding mode control (hybrid-SMC) scheme is constructed combining a new equivalent control algorithm with a high-order discontinuous control algorithm to benefit from the advantages of both control strategies. The hybrid-SMC scheme uses weighting coefficients to weight and combine controllers. The equivalent control algorithm uses a relative degree concept through dynamic constraints imposed on the sliding variables to overcome the limitations of the conventional approaches and to provide an optimum tracking performance. A scale-laboratory helicopter model is used to sum up the main features and demonstrate the effectiveness of the developed control scheme. The proposed hybrid-SMC strategy is compared to existing sliding mode-based control approaches in terms of tracking performance, stability and control efforts. The obtained results demonstrate the validity and efficiency of the proposed hybrid-SMC scheme.

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Hypersonic glider control using higher order sliding mode control

Cited by 7 publications

References 18 publications

L1 adaptive control augmentation for a hypersonic glider

L1 adaptive control augmentation for a hypersonic glider

An improved decentralized control method for Bank‐to‐Turn missile autopilot design

Hybrid high-order sliding mode-based control for multivariable cross-coupling systems: Scale-laboratory helicopter system application

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