Robust Control of a Reusable Launch Vehicle in Reentry Phase Using Model Following Neuro-Adaptive Design

Mathavaraj, S.; Halbe, Omkar; Padhi, Radhakant

doi:10.2514/6.2010-8312

Cited by 22 publications

(21 citation statements)

References 9 publications

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“…Considering nonlinear system (34), there exit a range of arbitrary positive constants ε 2 , γ 2 , ω 2 , η and μ, α m such that the tracking error σ ω and its derivative _ σ ω converge to the domain W ¼ 628 Q. DONG ET AL. 1 , η 2 are small positive constants) in finite time if the control law is designed as (38) with the adaptive gains (39).…”

Section: Adaptive-gain Multivariable Super-twisting Controller Designmentioning

confidence: 99%

Adaptive-gain multivariable super-twisting sliding mode control for reentry RLV with torque perturbation

Dong

Zong

Tian

et al. 2016

Int. J. Robust. Nonlinear Control

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Summary Reusable launch vehicle (RLV) should be under control in the presence of model uncertainty and external disturbance, which is considered as torque perturbation in this paper during the reentry phase. Such a challenge imposes tight requirements to the enhanced robustness and accuracy of the vehicle autopilot. The key of this paper is to propose an adaptive‐gain multivariable super‐twisting sliding mode controller when considering that the bounds of uncertainty and perturbation are not known. The important features of the controller are that the adaptation algorithm can achieve non‐overestimating values of the control gains and the multivariable super‐twisting sliding mode approach can obtain a more elegant solution in finite time. According to the multiple‐time scale features, the dynamics of RLV attitude motion are divided into outer‐loop subsystem and inner‐loop subsystem. On this basis, the controllers are designed respectively to ensure the finite‐time reentry attitude tracking. In addition, a proof of the finite‐time convergence for the overall system is derived using the Lyapunov function technique and multiple‐time scale characteristic. Finally, simulation results of six degree‐of‐freedom RLV are provided to verify the effectiveness and robustness of the proposed controller in tracking the guidance commands as well as achieving a safe and stable reentry flight. Copyright © 2016 John Wiley & Sons, Ltd.

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Section: Adaptive-gain Multivariable Super-twisting Controller Designmentioning

confidence: 99%

Adaptive-gain multivariable super-twisting sliding mode control for reentry RLV with torque perturbation

Dong

Zong

Tian

et al. 2016

Int. J. Robust. Nonlinear Control

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“…In this way, the vehicle meets the desired terminal conditions containing altitude, velocity, flight path angle and so on [1]. A reentry vehicle must operate over a broad flight envelope, spanning hypersonic fight to subsonic flight to landing [2].…”

Section: Introductionmentioning

confidence: 99%

“…Consider the sliding mode manifold in(7), when the second order sliding mode is established:, 0 s s = = the tracking error ( ) e t converges to zero in finite time if the parameters are chosen as1 2…”

mentioning

confidence: 99%

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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“…Xu et al [5] take advantage of the robust adaptive sliding sector to produce a virtual control effort signal and use a control allocator based on the L2 optimal control allocation strategy to distribute the virtual signal to the two pairs of actuators. Mathavaraj et al [6] allocate the control command in the daisy chain mode, which chooses to use the aerodynamic fin system as much as possible in order to save fuel for the lateral thruster system. Bi et al [7] provide an ADRC-based controller which obtains the required control moment according to the angle of attack tracking deviation then allocate the respective commands to the aerodynamic deflection and lateral thruster using the dynamic control allocation.…”

Section: Introductionmentioning

confidence: 99%

Autopilot Design for a Compound Control Small-Scale Solid Rocket in the Initial Stage of Launch

Dong

Chang

Song

2019

International Journal of Aerospace Engineering

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In this paper, an autopilot design method for a compound control small-scale solid rocket is proposed. The rocket has multiple actuators, including a flexible nozzle for pitching and yawing channels, aerodynamic fins for rolling channel, and lateral thrusters which work in on-off mode for all three channels. In order to keep the aircraft steady in the initial stage of launch when the dynamic pressure is low, the autopilot is aimed at optimizing the cooperation among the actuators. Firstly, without considering the discontinuous lateral thrust, the control law for flexible nozzle and aerodynamic fins is achieved via the sliding mode control approach. On this basis, an object to be controlled with choiceness is obtained for the lateral thrusters controlled loop. Secondly, the operation logic of lateral thrusters is programmed, regarding rolling moment as priority. Thirdly, after a continuous controller is obtained, a discretization method for the lateral thrusters control law is designed combining the characteristics of sliding mode control and Lyapunov’s stableness theorem. Finally, the fundamental cause why compound control improves the system stability is given theoretically. Simulation results validate the improved response performance and robustness against uncertainties and disturbance of the autopilot.

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Robust Control of a Reusable Launch Vehicle in Reentry Phase Using Model Following Neuro-Adaptive Design

Cited by 22 publications

References 9 publications

Adaptive-gain multivariable super-twisting sliding mode control for reentry RLV with torque perturbation

Adaptive-gain multivariable super-twisting sliding mode control for reentry RLV with torque perturbation

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

Autopilot Design for a Compound Control Small-Scale Solid Rocket in the Initial Stage of Launch

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