Robust Linear Output Feedback Control of an Airbreathing Hypersonic Vehicle

Sigthorsson, David O.; Jankovsky, Pete; Serrani, Andrea; Yurkovich, Stephen; Bolender, Michael A.; Doman, David B.

doi:10.2514/1.32300

Cited by 267 publications

(130 citation statements)

References 37 publications

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“…In the longitudinal dynamics (1) the flexible modes associated with aero-thermo-elastic effects are neglected for simplicity. The thrust T , drag D , and lift L forces, as well as the pitching moment M about the body y-axis are nonlinear uncertain functions that can be given as [2][3][4] Unlike in the existing literature on Hypersonic Vehicle control [4][5][6], where the control output…”

Section: Mathematical Model Of Air-breathing Hypersonic Missilementioning

confidence: 99%

Continuous higher order sliding mode control with adaptation of air breathing hypersonic missile

Shtessel

Edwards

2016

Adaptive Control & Signal

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Hypersonic missile control in the terminal phase is addressed using continuous higher order sliding mode (AHOSM) control with adaptation. The AHOSM self-tuning controller is proposed and studied. The double-layer adaptive algorithm is based on equivalent control concepts and ensures non-overestimation of the control gain to help mitigates control chattering. The proposed continuous AHOSM control is validated via simulations of a hypersonic missile in the terminal phase. The robustness and high accuracy output tracking in the presence of matched and unmatched external disturbances and missile model uncertainties is demonstrated.

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Section: Mathematical Model Of Air-breathing Hypersonic Missilementioning

confidence: 99%

Continuous higher order sliding mode control with adaptation of air breathing hypersonic missile

Shtessel

Edwards

2016

Adaptive Control & Signal

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“…This instability requires a minimum BW for stabilization 29 . To address these potentially conflicting specifications, one approach has been to exploit the addition of a canard 19,32,[36][37][38] . It is understood, of course, that any canard approach would face severe heating, structural, and reliability issues.…”

Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

Control-Relevant Modeling, Analysis, and Design for Scramjet-Powered Hypersonic Vehicles

Rodriguez

Dickeson

Sridharan

et al. 2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

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Within this paper, control-relevant vehicle design concepts are examined using a widely used 3 DOF (plus flexibility) nonlinear model for the longitudinal dynamics of a generic carrot-shaped scramjet powered hypersonic vehicle. Trade studies associated with vehicle/engine parameters are examined. The impact of parameters on control-relevant static properties (e.g. level-flight trimmable region, trim controls, AOA, thrust margin) and dynamic properties (e.g. instability and right half plane zero associated with flight path angle) are examined. Specific parameters considered include: inlet height, diffuser area ratio, lower forebody compression ramp inclination angle, engine location, center of gravity, and mass. Vehicle optimizations is also examined. Both static and dynamic considerations are addressed. The gap-metric optimized vehicle is obtained to illustrate how this controlcentric concept can be used to "reduce" scheduling requirements for the final control system. A classic inner-outer loop control architecture and methodology is used to shed light on how specific vehicle/engine design parameter selections impact control system design. In short, the work represents an important first step toward revealing fundamental tradeoffs and systematically treating control-relevant vehicle design.

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“…Then pressure varies, lead to the changes of the stress on aircraft. We can verify the aircraft's dynamic character accurately in the fixed height nearby through the fixed height flying test [4][5][6][7] . The change of aerodynamic force caused by the change of height is vital part of the interferences。But for hypersonic aircraft, its influence is not exceeding the engine and the changes of the elastics' [8,9] .…”

Section: Introductionmentioning

confidence: 99%

Research on fixed attack angle attack angle and height flying of hypersonic aircraft

Wu¹,

Li²,

Lei³

2015

Proceedings of the 2015 3rd International Conference on Machinery, Materials and Information Technology Applications

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Attack angle is a most important factor that affect the stability of aircraft no matter for supersonic type or hypersonic type aircraft. And height is another factor that will affect the force and moment of the whole dynamic system by change the density of air and finally it will also affect the stability of the whole system. So in this paper a kind of virtual flying with fixed attack angle and height is proposed to testify the rightness of the hypersonic aircraft model and air coefficient. It is a new and meaningful model testifying method for complex flying systems.

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Robust Linear Output Feedback Control of an Airbreathing Hypersonic Vehicle

Cited by 267 publications

References 37 publications

Continuous higher order sliding mode control with adaptation of air breathing hypersonic missile

Continuous higher order sliding mode control with adaptation of air breathing hypersonic missile

Control-Relevant Modeling, Analysis, and Design for Scramjet-Powered Hypersonic Vehicles

Research on fixed attack angle attack angle and height flying of hypersonic aircraft

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