Modeling and Control of Scramjet-Powered Hypersonic Vehicles: Challenges, Trends, and Tradeoffs

Rodriguez, Armando A.; Dickeson, Jeffrey J.; Cifdaloz, O.; Kelkar, Atul G.; Vogel, J. M.; Soloway, Don; McCullen, Robert; Benavides, Jose; Sridharan, S.

doi:10.2514/6.2008-6793

Cited by 122 publications

(99 citation statements)

References 62 publications

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“…Within 29 , it is shown that the nonlinear model changes significantly as a function of the flight condition. Specifically, it is shown that the vehicle pitch-up instability and non-minimum phase (NMP) zero vary significantly across the vehicle's trimmable region.…”

Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

“…The controls include: elevator, stoichiometrically normalized fuel equivalency ratio (FER), diffuser area ratio (not considered in this work), and a canard (not considered in this work). A more complete description of the vehicle model can be found in previous works 7,29 .…”

Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

“…In addition, the rearward situated scramjet and cg (center of gravity), implies an inherent pitch-up vehicle instability. 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] .…”

Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

“…Within this paper, we exploit the generic carrot-shaped vehicle 3DOF (plus flexibility) model presented in 7,19,26,29 . A myriad of issues exist that make control design for this hypersonic vehicle a potentially challenging problem:…”

Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

“…The computational time associated with the enhanced model is significant, thus making it cumbersome for control-relevant analysis. The simple 1D Rayleigh flow engine model discussed within 7,19,26,29 will be used in the current paper.…”

Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

See 4 more Smart Citations

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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Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

Section: Controls-relevant Hypersonic Vehicle Modelingmentioning

confidence: 99%

See 3 more Smart Citations

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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View full text Add to dashboard Cite

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Disturbance Decoupling Control for Flexible Air‐Breathing Hypersonic Vehicles with Mismatched Condition

Feng

Zhang

Cao

et al. 2018

Asian Journal of Control

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The disturbance decoupling control method is investigated for flight control of a flexible air-breathing hypersonic vehicle (FAHV). First, the longitudinal dynamics of the FAHV are simplified into nonlinear forms with mismatched system disturbances. Then a new nonlinear disturbance observer base on hyperbolic sine function is applied to estimate the mismatched disturbances. The disturbance decoupling control law for flight control of FAHV is deduced theoretically and its proof is provided. Finally, the stability of the closed-loop control system under the action of disturbance decoupling control law is proved by Lyapunov stability theory. Simulation results exhibit the performance and effectiveness of the proposed disturbance decoupling control law.

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Adaptive high‐order dynamic sliding mode control for a flexible air‐breathing hypersonic vehicle

Zong

Wang

Tao

2013

Intl J Robust & Nonlinear

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The problem of tracking control for a longitudinal air-breathing hypersonic vehicle model with flexible effects and intricate couplings between the engine dynamics and flight dynamics is investigated in this paper. In order to overcome the analytical intractability of this model, a simplified model is constructed during the feedback controller design. High-order dynamic sliding mode control is proposed to force the velocity and altitude of the flexible air-breathing hypersonic vehicle (FAHV) to the desired reference commands in finite time. In addition, the adaptive control method is employed to identify bounded uncertainties for eliminating the requirement of boundaries needed in the robust controller design and to guarantee the property of finite time stability without information of upper bound of uncertainties. Finally, simulations are presented to illustrate the effectiveness of the control strategies. ADAPTIVE HOSM CONTROL FOR A FLEXIBLE HYPERSONIC VEHICLE 1719As a result of slender geometries and light structures of this generic vehicle, significant flexible effects cannot be neglected in the controller design [7], because these modes may be harmful to system stability. In order to ensure safety and reliability, controller design for AHVs must guarantee stability of the flight system and provide a satisfying control performance [8]. Recently, an airbreathing hypersonic vehicle (FAHV) model with flexible dynamics was developed in [9,10]. On the basis of this kind of FAHV models, several studies on flight control design and simulation have been published in recent years. Because of the enormous complexity of the nonlinear dynamics, linearized model has been widely employed as the basis for flight control design. In [11], nonlinear longitudinal dynamics of a FAHV was directly linearized at a specified trim condition, and a linear quadratic regulator (LQR) was presented for a region in the neighborhood of the operating point. On the other hand, many efforts have been devoted to nonlinear control design for FAHVs. Sequential loop closure controller design [12][13][14] was based on the decomposition of FAHV equations into functional subsystems. The method followed combined robust adaptive dynamic inversion with back-stepping arguments to obtain control architecture. Approximate feedback linearization was applied in [15,16], to transform the FAHV model into a MIMO model, and an LQR strategy with integral augmentation based on dynamic inversion method was adopted to provide excellent tracking performance. In [17,18], a robust nonlinear tracking controller was constructed by using a minimax LQR control approach for the FAHV model developed by David and Serrani [19]. And the minimax optimal control design method was an extension of the LQR method to a class of uncertain systems. This controller design method provided robust stability and performance for the FAHV systems under varying flight conditions.In practice, the atmospheric properties and aerodynamic characteristics in the flight envelop of FAHVs are difficult...

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Modeling and Control of Scramjet-Powered Hypersonic Vehicles: Challenges, Trends, and Tradeoffs

Cited by 122 publications

References 62 publications

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

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

Disturbance Decoupling Control for Flexible Air‐Breathing Hypersonic Vehicles with Mismatched Condition

Adaptive high‐order dynamic sliding mode control for a flexible air‐breathing hypersonic vehicle

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