Comprehensive design of uniform robust exact disturbance observer and fixed‐time controller for reusable launch vehicles

You, Min; Zong, Qun; Tian, Bailing; Zhao, Xinyi; Zeng, Fanlin

doi:10.1049/iet-cta.2017.0466

Cited by 26 publications

(16 citation statements)

References 32 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…However, they do not only depend on time, but also on the states of the flight. Considering that the flight conditions and the states may not change rapidly, we propose the above assumption [4,14,[27][28][29] for the controller design in this study. In practice, because the derivatives of these uncertainties are difficult to acquire beforehand, their upper bounds, δ 1 and δ 2 , are set relatively large to adapt with extreme flying conditions.…”

Section: Control Law Designmentioning

confidence: 99%

“…However, the correlation is difficult to model and simulate. Then, inspired by the simulations of [4,17,20,27], the uncertainties, D 1 and D 2 , are selected with white Gaussian noises for illustrating the robustness and filter's character of the developed nonlinear disturbance observer. Our future research will focus on considering the correlated D 1 and D 2 which are state-dependent and develop an adaptive-gain controller under the proposed scheme.…”

Section: Remarkmentioning

confidence: 99%

“…There are many interesting and challenging problems with respect to the control of modern aircraft. These include, but are not limited to, the cross-coupling of dynamics [1], non-minimum phase behavior [2], constraints on the control inputs as a result of position and rate limits [3], and high nonlinearity and uncertainty [4] in flight equations. Moreover, the performance of a flight control system is expected to be very high, and the demands for flight safety have dictated the development of the robust control designs [5].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Vector-Coupled Flight Controller Design Based on Multivariable Backstepping Sliding Mode

Han

2019

Symmetry

View full text Add to dashboard Cite

This study aims to address the issues of the simultaneous control of the angle of attack, sideslip angle, and airspeed of a flight in a vectorial form. A vector controller, with a symmetry structure, is developed to transform the attitude and speed control problem into a space-vector tracking problem. We first establish flight vector-coupled dynamics, i.e., describe velocity and angular-velocity vectors in a body-fixed frame, and then propose a multivariable backstepping sliding mode control algorithm along with nonlinear disturbance observers for the vectorial dynamics. The theoretical analysis ensures that the states of the system can be enforced to reach a small neighborhood of the desired sliding manifold. The results of the numerical simulation illustrate the effectiveness and robustness of the combined vector-control scheme.

show abstract

Section: Control Law Designmentioning

confidence: 99%

Section: Remarkmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Vector-Coupled Flight Controller Design Based on Multivariable Backstepping Sliding Mode

Han

2019

Symmetry

View full text Add to dashboard Cite

show abstract

“…Recently, the investigation of systems subject to uncertainties and disturbances has received considerable research attention and many effective control methods are proposed [18][19][20][21][22][23][24][25][26][27][28][29][30]. In [18], Lam comprehensively analyzes the estimation problem of reachable set and extends the algorithm to the situation with parameter uncertainties.…”

Section: Introductionmentioning

confidence: 99%

Enhanced predictor–corrector Mars entry guidance approach with atmospheric uncertainties

Qiao

Guo

et al. 2019

IET Control Theory & Applications

View full text Add to dashboard Cite

Due to the long-range data communication and complex Mars environment, the Mars lander needs to promote the ability to autonomously adapt uncertain situations ensuring high precision landing in future Mars missions. Based on the analysis of multiple disturbances, this paper demonstrates an enhanced predictor-corrector guidance method to deal with the effect of atmospheric uncertainties during the entry phase of the Mars landing. In the proposed method, the predictor-corrector guidance algorithm is designed to autonomously drive the Mars lander to the parachute deployment. Meanwhile, the disturbance observer is designed to onboard estimate the effect of fiercely varying atmospheric uncertainties resulting from rapidly height decreasing. Then, with the estimation of atmospheric uncertainties compensated in the feed-forward channel, the composite guidance method is put forward such that both anti-disturbance and autonomous performance of the Mars lander guidance system are improved. Convergence of the proposed composite method is analyzed. Simulations for a Mars lander entry guidance system demonstrates that the proposed method outperforms the baseline method in consideration of the atmospheric uncertainties.

show abstract

“…Based on this work, a nonsingular terminal sliding-mode controller was designed to guarantee the attitude angles of RLV track the command in a fixed-time under the influence of wind disturbance. 37 The comprehensive design of uniform robust exact disturbance observer and fixed-time controller for RLV was investigated in the work of You et al 38 Motivated by these, this paper investigates a multivariable supertwisting fixed-time approach, which combines the advantage of multivariable supertwisting sliding-mode control method and fixed-time convergence theory. A novel control scheme for RLV attitude control is proposed based on the multivariable supertwisting fixed-time approach, the control scheme divides the attitude control system into attitude angle subsystem and attitude angle rate subsystem, for which the comprehensive design of fixed-time disturbance observer and controller is presented.…”

Section: Introductionmentioning

confidence: 99%

Multivariable supertwisting fixed‐time approach for RLV re‐entry attitude control

You

Zong

Zuo

et al. 2018

Intl J Robust & Nonlinear

Self Cite

View full text Add to dashboard Cite

The attitude control problem of reusable launch vehicles (RLVs) is investigated based on multivariable supertwisting fixed-time comprehensive control strategy.A novel multivariable supertwisting fixed-time approach, which can guarantee that the states converge to zero within a fixed time, is proposed. According to the multiple time scale principle, the RLV attitude control system is divided into attitude angle subsystem and attitude angle rate subsystem. Based on multivariable supertwisting fixed-time approach, comprehensive design of fixed-time disturbance observer and controller is proposed to ensure that the attitude angle tracking error converges to zero within a fixed time. The features of the proposed control scheme contain that the settling time is independent of initial conditions and it has the better property of chattering reduction. Finally, the efficiency of the proposed method is verified through numerical simulation.

show abstract

Comprehensive design of uniform robust exact disturbance observer and fixed‐time controller for reusable launch vehicles

Cited by 26 publications

References 32 publications

Vector-Coupled Flight Controller Design Based on Multivariable Backstepping Sliding Mode

Vector-Coupled Flight Controller Design Based on Multivariable Backstepping Sliding Mode

Enhanced predictor–corrector Mars entry guidance approach with atmospheric uncertainties

Multivariable supertwisting fixed‐time approach for RLV re‐entry attitude control

Contact Info

Product

Resources

About