Nonlinear Robust/Adaptive Controller Design for an Air-Breathing Hypersonic Vehicle Model

Fiorentini, Lisa; Serrani, Andrea; Bolender, Michael A.; Doman, David B.

doi:10.2514/6.2007-6329

Cited by 81 publications

(87 citation statements)

References 28 publications

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“…This instability requires a minimum BW for stabilization 28 . To address these potentially conflicting specifications, one approach has been to exploit the addition of a canard 18,34,[38][39][40] . 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%

See 1 more Smart Citation

Elevator Sizing, Placement, and Control-Relevant Tradeoffs for Hypersonic Vehicles

Dickeson

Rodriguez

Sridharan

et al. 2010

AIAA Guidance, Navigation, and Control 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. The impact of elevator size and placement 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. Elevator usage has been examine for a class of typical hypersonic trajectories.

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Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

“…For this system, velocity control is achieved via the FER input. Flight path angle (FPA) control is achieved with the elevator 34 . However, there is significant coupling between F ER and FPA.…”

Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

Elevator Sizing, Placement, and Control-Relevant Tradeoffs for Hypersonic Vehicles

Dickeson

Rodriguez

Sridharan

et al. 2010

AIAA Guidance, Navigation, and Control Conference

View full text Add to dashboard Cite

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. The impact of elevator size and placement 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. Elevator usage has been examine for a class of typical hypersonic trajectories.

show abstract

“…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%

“…For this system, velocity control is achieved via the FER input. Flight path angle (FPA) control is achieved with the elevator 32 . However, there is significant coupling between F ER and FPA.…”

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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“…A traditional tail rudder deflection does not actively control the engine inlet conditions which allow the engines to power on when maneuvering, especially during push-over maneuver which will result in negative angles of attack. Many researchers have focused on the precise attitude control of hypersonic vehicle [1] [2] [3] [7], but very few literatures have studied the maneuverability while air-breathing hypersonic aircraft cruising.…”

Section: A >mentioning

confidence: 99%

A Composite Control Strategy for an Air-Breathing Hypersonic Vehicle with Wing-Rudder Deflection

Fan¹,

Yan²,

Yu³

et al. 2015

Proceedings of the International Conference on Computer Information Systems and Industrial Applications

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Abstract--The scramjet performance of air-breathing hypersonic vehicle is highly correlated with flight height, Mach and angle of attack (AOA). The violent disturbance of the AOA can cause the engine power off. Consequently, the maneuverability of hypersonic vehicle is strictly limited in the cruising period. A composite control system for an air-breathing hypersonic vehicle is presented. The hypersonic vehicle has a configuration with tailcontrol rudders and a set of deflectable wings installed nearby the center of gravity. During the cruising period, the precision of AOA is achieved by deflecting tail rudders, and the command of maneuverable acceleration is tracked by deflecting wings. In the period of endgame, the scramjet should be power off, and the limit of AOA does not exist, so the tail rudders and the wings can both deflect to achieve high maneuverable acceleration. A linear quadratic (LQ) track control algorithm with integrator is introduced to design the composite control system. Simulation results demonstrate that the composite control system has good performance in tracking AOA and acceleration command by respective deflection of tail rudders and deflectable wings in cruise and also can track high acceleration command by coincident deflection during endgame.

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Nonlinear Robust/Adaptive Controller Design for an Air-Breathing Hypersonic Vehicle Model

Abstract: This report is published in the interest of scientific and technical information exchange, and its publication does not constitute the Government's approval or disapproval of its ideas or findings.

Cited by 81 publications

References 28 publications

Elevator Sizing, Placement, and Control-Relevant Tradeoffs for Hypersonic Vehicles

Elevator Sizing, Placement, and Control-Relevant Tradeoffs for Hypersonic Vehicles

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

A Composite Control Strategy for an Air-Breathing Hypersonic Vehicle with Wing-Rudder Deflection

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