Collision avoidance ZEM/ZEV optimal feedback guidance for powered descent phase of landing on Mars

Zhang, Yao; Guo, Yanning; Ma, Guangfu; Zeng, Tianyi

doi:10.1016/j.asr.2016.12.040

Cited by 33 publications

(13 citation statements)

References 12 publications

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“…Theorem 4. For the system (30), the proposed guidance (25) can ensure the terminal position of the lander to land within a neighborhood area of the target landing site in a fixed time, and the neighborhood and the upper bound of the convergence time are expressed in (31) and (32).…”

Section: Robustness Analysis Based On Practical Fixed-time Stabilimentioning

confidence: 99%

“…Guo et al proposed a zero-effort-miss/zero-effort-velocity (ZEM/ZEV) optimal feedback guidance for Mars powered descent phase, which ensured the fuel optimality [12]. Yao et al proposed an improved ZEM/ZEV guidance by adding a collision avoidance term, which was proven effective to cope with the hazard avoidance problem [25]. Guo et al designed a waypoint method based ZEM/ZEV guidance to simplify the optimal solution during the landing process [13].…”

Section: Introductionmentioning

confidence: 99%

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Mars Powered Descent Phase Guidance Design Based on Fixed-Time Stabilization Technique

Zhang

Vepa

et al. 2019

IEEE Trans. Aerosp. Electron. Syst.

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This paper proposes a guidance scheme to achieve an autonomous precision landing on Mars and proposes a practical fixed-time stabilization theorem to analyze the robustness of the guidance. The proposed guidance is mainly based on the fixedtime stabilization method, and it can achieve the precision landing within a pre-defined time. This property enables the proposed guidance to outperform the finite-time stabilization technique which cannot handle uncertainties well and whose convergence time is dependent on initial states. Compared with the existing fixed-time stabilization theorem, the proposed practical fixedtime stabilization theorem can achieve a shorter convergence time and cope with unknown disturbances. When the Mars landing guidance is designed by this proposed theorem, the upper bound of the landing time and the maximum landing error subject to unknown disturbances can be calculated in advance. Theoretical proofs and Monte Carlo simulation results confirm the effectiveness of the proposed theorem and the proposed guidance. Furthermore, the efficacy of the proposed guidance with thrust limitations is also demonstrated by testing of 50 cases with a range of initial positions and velocities.

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Section: Robustness Analysis Based On Practical Fixed-time Stabilimentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Mars Powered Descent Phase Guidance Design Based on Fixed-Time Stabilization Technique

Zhang

Vepa

et al. 2019

IEEE Trans. Aerosp. Electron. Syst.

Self Cite

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“…in the dynamics are generally on a smaller order of magnitude and are uncertain and unknown in advance, the dynamic constraints (10)(11)(12) in the off-line design do not include these uncertain and unknown items.…”

Section: B Trajectory Optimizationmentioning

confidence: 99%

“…The main concern of the optimal feedback guidance algorithms is always the guidance performance optimization under uncertain perturbations, but this kind of approaches usually doesn't consider retargeting [9]. To combine hazard avoidance with fuel sub-optimality, Zhang proposed a hybrid guidance algorithm for Mars powered descent using ZEM/ZEV and optimal feedback [10]. In summary, these existing methods for planetary powered descent still have design limitations when combining fuel optimality with retargeting flexibility and robustness against uncertainty.…”

Section: Introductionmentioning

confidence: 99%

Computational guidance for planetary powered descent using collaborative optimization

Jiang

Tao³

2018

Aerospace Science and Technology

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An innovative computational guidance framework is proposed for planetary powered descent using collaborative optimization approach. First, the dynamical model and constraints for planetary powered descent are presented. Then, using collaborative optimization strategy, the computational guidance framework for powered descent is formulated as a multi-discipline optimization problem including trajectory optimization, optimal guidance, and system-level optimization. Finally, the computational guidance approach employs three algorithms for respectively solving the three optimization modules to implement numerical simulations. The optimality and robustness of the computational guidance approach are verified with all constraints satisfied even in the presence of initial state uncertainty.

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“…[10][11][12] Gradually, based on the Apollo method and its extension, a great deal of attention has been focused on the guidance problem using zero-effort-miss/zero-effort-velocity theory, optimal nonlinear feedback guidance algorithm, and sliding mode guidance approach during Mars landing process. [13][14][15][16][17] Nevertheless, most studies ignore the effect of disturbances or just regard the disturbance as a norm bounded vector. Abandoning the prior information or not using measurable signals will bring great conservativeness to the system.…”

Section: Introductionmentioning

confidence: 99%

An enhanced anti-disturbance guidance scheme for powered descent phase of Mars landing under actuator fault

Jin

Qiao

Guo

2018

International Journal of Advanced Robotic Systems

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As a class of autonomous deep-space exploration robots, Mars lander is simultaneously affected by wind disturbance and actuator fault, which hinders precise landing on Mars. In this article, we propose a composite guidance approach by combining disturbance observer and iterative learning observer together. The Mars wind disturbance is dealt by the disturbance observer providing wind estimation which is rejected through feed-forward channel. Meanwhile, the iterative learning observer is used to estimate the deficiency of actuators. The proposed guidance scheme ensures not only the precision but also the reliability of the Mars guidance system. The stability of the closed-loop system is analyzed. Simulations made in different situations demonstrate the performance of the proposed approach.

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Collision avoidance ZEM/ZEV optimal feedback guidance for powered descent phase of landing on Mars

Cited by 33 publications

References 12 publications

Mars Powered Descent Phase Guidance Design Based on Fixed-Time Stabilization Technique

Mars Powered Descent Phase Guidance Design Based on Fixed-Time Stabilization Technique

Computational guidance for planetary powered descent using collaborative optimization

An enhanced anti-disturbance guidance scheme for powered descent phase of Mars landing under actuator fault

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