Reusable launch vehicle control in sliding modes

Shtessel, Yuri B.; Tournes, Christian; Krupp, D.

doi:10.2514/6.1997-3533

Cited by 16 publications

(27 citation statements)

References 6 publications

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“…is a sensitivity matrix calculated through a nonlinear aerodynamic database presented in the form of lookup tables [41]. shows different states of m RCS thrusters.…”

Section: Mathematical Model and Problem Formulationmentioning

confidence: 99%

“…Chattering may make the aerodynamic surfaces of the reentry vehicle deflect with a large frequency, possiblely out of the realm of technology or resulting in damage to actuators. To alleviate the chattering, the SMC attitude controllers in [19][20][21]23,24] introduce the boundary layer technique. This approach replaces the sign function by some smooth approximations, e.g., saturation function or sigmoid function, when the state trajectory lies within a suitable boundary layer.…”

Section: Introductionmentioning

confidence: 99%

“…It is insensitive to parameter variations and external disturbances under matching conditions [16], and has fast dynamic response, making it a potential approach for flight control system [17,18]. The sliding mode control method is utilized to design the attitude controller for the RLV in [19,20], where a sliding mode manifold is firstly designed such that states of the flight control system on the sliding mode manifold exhibit desired attitude tracking behavior, then the control strategy is designed to drive the system states to the sliding mode manifold and guarantee system motion on it thereafter. Subsequently, a time-varying SMC is proposed to achieve the fault tolerance for RLV attitude control [21].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Nonsingular finite-time second order sliding mode attitude control for reentry vehicle

Sheng

Geng²,

Liu

et al. 2015

Int. J. Control Autom. Syst.

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This paper presents nonlinear robust flight control strategies for the reentry vehicle which is nonlinear, coupling, and includes parameter uncertainties and external disturbances. Firstly, a finitetime second order sliding mode attitude control strategy is pointed out with the introduction of a nonsingular finite-time sliding mode manifold. By the proposed controller, the attitude tracking errors are mathematically proved to converge to zero within finite time and the chattering of sliding mode controller is alleviated without any deterioration of robustness and accuracy. For further alleviation of chattering, a smooth second order sliding mode attitude control strategy is then designed based on an improved nonsingular finite-time sliding mode manifold. Finally, the proposed strategies are applied to the attitude control of X-33 RLV in the reentry phase to verify the validity and robustness of the proposed strategies.

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“…is a sensitivity matrix calculated through a nonlinear aerodynamic database presented in the form of lookup tables [41]. shows different states of m RCS thrusters.…”

Section: Mathematical Model and Problem Formulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Nonsingular finite-time second order sliding mode attitude control for reentry vehicle

Sheng

Geng²,

Liu

et al. 2015

Int. J. Control Autom. Syst.

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show abstract

“…The nominal trajectory linearization (NTL) method applied to a reusable launch vehicle (RLV) by Zhu et al is an advanced nonlinear control technique that linearized the tracking error of a nonlinear time-varying plant along a nominal (commanded) trajectory [1,2]. This paper presents a nonlinear dynamic inverse guidance scheme and a multiple-time-scale continuous time-varying controller [3][4][5] design method for the ABHV based on nominal trajectory linearization. The ABHV control structure has two loops: the outer and the inner loops.…”

Section: Introductionmentioning

confidence: 98%

Time-varying control via nominal trajectory linearization for an air-breathing hypersonic vehicle

She

2011

J. Control Theory Appl.

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A time-varying control law via nominal trajectory linearization for an air-breathing hypersonic vehicle (ABHV) model is applied. Feasible guidance command signal serials are generated by nonlinear dynamic inverse (NDI) method considering interactions between aerodynamic effects and propulsion systems. Multiple-time-scale continuous time-varying control, which meets the requirement with accurate, robust, and decoupled tracking of both the commanded trajectory and angular rate profiles in the presence of modeling uncertainties and external disturbances are applied. The simulations for an ABHV model with modeling uncertainties, wind gust, and measuring noises are presented to demonstrate the capacity and reliability of this proposed method.

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“…It is one of the most important approaches to the control of systems with modeling imprecision, and it has been widely applied to the flight control system design [4][5][6][7][8][9][10][11]. References [12,13] incorporate the sliding mode surface into the quadratic performance index of the predictive control and then the predictive sliding mode control law which has an explicitly analytical form is derived by minimizing the performance index.…”

Section: Introductionmentioning

confidence: 99%

Predictive Sliding Mode Control for Attitude Tracking of Hypersonic Vehicles Using Fuzzy Disturbance Observer

Cheng

Tang

Wang

et al. 2015

Mathematical Problems in Engineering

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We propose a predictive sliding mode control (PSMC) scheme for attitude control of hypersonic vehicle (HV) with system uncertainties and external disturbances based on an improved fuzzy disturbance observer (IFDO). First, for a class of uncertain affine nonlinear systems with system uncertainties and external disturbances, we propose a predictive sliding mode control based on fuzzy disturbance observer (FDO-PSMC), which is used to estimate the composite disturbances containing system uncertainties and external disturbances. Afterward, to enhance the composite disturbances rejection performance, an improved FDO-PSMC (IFDO-PSMC) is proposed by incorporating a hyperbolic tangent function with FDO to compensate for the approximate error of FDO. Finally, considering the actuator dynamics, the proposed IFDO-PSMC is applied to attitude control system design for HV to track the guidance commands with high precision and strong robustness. Simulation results demonstrate the effectiveness and robustness of the proposed attitude control scheme.

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Reusable launch vehicle control in sliding modes

Cited by 16 publications

References 6 publications

Nonsingular finite-time second order sliding mode attitude control for reentry vehicle

Nonsingular finite-time second order sliding mode attitude control for reentry vehicle

Time-varying control via nominal trajectory linearization for an air-breathing hypersonic vehicle

Predictive Sliding Mode Control for Attitude Tracking of Hypersonic Vehicles Using Fuzzy Disturbance Observer

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