Flight Control of Atmospheric Re-entry Vehicle with Non-linear Dynamic Inversion

Juliana, S.; Chu, Q.P.; Mulder, J.A.; Baten, T.J. van

doi:10.2514/6.2004-5330

Cited by 20 publications

(20 citation statements)

References 4 publications

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“…T are the translational terms (aerodynamic lift L, aerodynamic side-force Y, weight W, aircraft mass M, and airspeed V) that influence the rotational motion [39]. As widely accepted [40][41][42], the influence is negligible when designing the attitude controller.…”

Section: Mathematical Modelingmentioning

confidence: 99%

“…As a result, the estimated lumped disturbance of the NDI-AW in Figure 9d was of much smaller magnitude than that of the NDI-DO. Furthermore, according to Equation (39), the estimation error of the disturbance observer was related to the time derivative of the disturbances. Since the lumped disturbance of the NDI-DO consists of the nonlinear, noncontinuous deflection saturations, the resulting estimation error blows up.…”

Section: Investigation Of the Anti-windup Performancementioning

confidence: 99%

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Design and Validation of Disturbance Rejection Dynamic Inverse Control for a Tailless Aircraft in Wind Tunnel

et al. 2021

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This paper focuses on the design of a disturbance rejection controller for a tailless aircraft based on the technique of nonlinear dynamic inversion (NDI). The tailless aircraft model mounted on a three degree-of-freedom (3-DOF) dynamic rig in the wind tunnel is modeled as a nonlinear affine system subject to mismatched disturbances. First of all, a baseline NDI attitude controller is designed for sufficient stability and good reference tracking performance of the nominal system. Then, a nonlinear disturbance observer (NDO) is supplemented to the baseline NDI controller to estimate the lumped disturbances for compensation, including unmodeled dynamics, parameter uncertainties, and external disturbances. Mathematical analysis demonstrates the convergence of the employed NDO and the resulting closed-loop system. Furthermore, an anti-windup modification is applied to the NDO for control performance preserving in the presence of actuator saturation. Subsequently, the designed control schemes are preliminarily validated and compared via simulations. The baseline NDI controller demonstrates satisfactory attitude tracking performance in the case of nominal simulation; the NDO augmented NDI controller presents significantly improved ability of disturbance rejection when compared with the baseline NDI controller in the case of robust simulation; the anti-windup modified scheme, rather than the baseline NDI controller nor the NDO augmented NDI controller, can preserve the closed-loop performance in the case of actuator saturation. Finally, the baseline NDI scheme and the NDO augmented NDI scheme are implemented and further validated in the wind tunnel flight tests, which demonstrate that the experimental results are in good agreement with that of the simulations.

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Section: Mathematical Modelingmentioning

confidence: 99%

Section: Investigation Of the Anti-windup Performancementioning

confidence: 99%

Design and Validation of Disturbance Rejection Dynamic Inverse Control for a Tailless Aircraft in Wind Tunnel

et al. 2021

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show abstract

“…The parameter identification problem has been widely studied in recent years, and many methods have been proposed, and good results have been achieved. Since it is very convenient to construct Lyapunov function to prove the stability of system, the adaptive control and parameter identification method is one of most favorite method of most researchers [1][2][3][4] . But the problem of parameter identification is more complex, and it is more difficult to identify the parameter in many cases than the stability of the system.…”

Section: Introductionmentioning

confidence: 99%

“…write matlab m language program as follows: clc;clear; k11=-10;k12=-5;k13=-5;k14=-5;k15=-5;k16=-5;esten1=0.2;taox=3;Construct a Simulink program with Matlab software as follows:[1]+5*sin(u[1])+u[2] …”

mentioning

confidence: 99%

Research on parameters identification of system with uncertainty and unknown parameter

Wu¹,

Liang²,

Lei³

2016

Proceedings of the 2016 4th International Conference on Machinery, Materials and Computing Technology

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In order to illustrate the complexity of system parameter identification, this paper takes a simple one order system as an example, which contains an unknown parameter and an uncertain term. It adopts the adaptive method to design the identification rules of unknown parameters, and uses the robust control method to deal with the uncertainty. And system stability is proved by constructing a Lyapunov function. The simulation results show that the stability control of the system is simple, but it is not possible to accurately identify the parameters of the system in the presence of uncertainty.

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“…According to the definition of Zadeh: "the system identification is based on the input and output data, from a set of given model classes, to determine a system equivalent to the test model. According to the identification theory, the identification method can be divided into two categories [5][6][7][8] , the classical identification method and the modern identification method. Adaptive parameter identification [9][10][11][12] is a small branch of modern identification method.…”

Section: Introductionmentioning

confidence: 99%

Discussion on the choosing of Lyapunov function for adaptive parameter identification problem

Jin¹,

Lei²,

Wu³

2016

Proceedings of the 2016 4th International Conference on Machinery, Materials and Computing Technology

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The selection of Lyapunov function is depth studied with adaptive parameter identification, where a kind of simple first order system with two unknown parameters is taken as an example. The study shows that the selection of Lyapunov function is completely free, and the proportion of the parameter identification and the steady-state error part can be matched arbitrarily. But the above two coefficients should be set to be positive, and the different proportion coefficient setting method will lead to different result of steady state error and parameter identification.

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Flight Control of Atmospheric Re-entry Vehicle with Non-linear Dynamic Inversion

Cited by 20 publications

References 4 publications

Design and Validation of Disturbance Rejection Dynamic Inverse Control for a Tailless Aircraft in Wind Tunnel

Design and Validation of Disturbance Rejection Dynamic Inverse Control for a Tailless Aircraft in Wind Tunnel

Research on parameters identification of system with uncertainty and unknown parameter

Discussion on the choosing of Lyapunov function for adaptive parameter identification problem

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