Trajectory optimization for accompanying satellite obstacle avoidance

Hu, Qinglei; Xie, Jingjie; Liu, Xinfu

doi:10.1016/j.ast.2018.08.033

Cited by 27 publications

(9 citation statements)

References 32 publications

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“…When s > ε 1 and s ≤ ε 1 , q v ≤ ε 2 , calculate the derivative of V function and noticing (25) it could be got that .…”

Section: Sig S ω Jω Jfω Sign S S Sig S ω Jωmentioning

confidence: 99%

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Robust Finite-Time Control Algorithm Based on Dynamic Sliding Mode for Satellite Attitude Maneuver

Liang

2021

Mathematics

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Robust finite-time control algorithms for satellite attitude maneuvers are proposed in this paper. The standard sliding mode is modified, hence the inherent robustness could be maintained, and this fixed sliding mode is modified to dynamic, therefore the finite-time stability could be achieved. First, the finite -time sliding mode based on attitude quaternion is proposed and the loose finite-time stability is achieved by enlarging the sliding mode parameter. In order to get the strict finite-time stability, a sliding mode based on the Euler axis is then given. The fixed norm property of the Euler axis is used, and a sliding mode parameter without singularity issue is achieved. System performance near the equilibrium point is largely improved by the proposed sliding modes. The singularity issue of finite-time control is solved by the property of rotation around a fixed axis. System finite-time stability and robustness are analyzed by the Lyapunov method. The superiority of proposed controllers and system robustness to some typical perturbations such as disturbance torque, model uncertainty and actuator error are demonstrated by simulation results.

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“…When s > ε 1 and s ≤ ε 1 , q v ≤ ε 2 , calculate the derivative of V function and noticing (25) it could be got that .…”

Section: Sig S ω Jω Jfω Sign S S Sig S ω Jωmentioning

confidence: 99%

“…However, the method is suitable for several typical uncertainty models but not suitable for the random noise model. Hu [24][25][26] designed some robust controllers to system uncertainty. The sign function terms are added in the controllers and the system uncertainty is treated as Gauss white noise with an upper bounded norm.…”

Section: Introductionmentioning

confidence: 99%

Robust Finite-Time Control Algorithm Based on Dynamic Sliding Mode for Satellite Attitude Maneuver

Liang

2021

Mathematics

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“…The basic objective in (65a) is to minimize fuel consumption (Park et al, 2013). Other choices include sparsification of the control sequence (Hartley et al, 2013), trading off flight duration with fuel consumption (Hu et al, 2018), encouraging smoothness of the control sequence (Li and Zhu, 2018a), and reducing the sensitivity to sensing and control uncertainties (Jin et al, 2020). We note that Problem 65 only characterizes the last phase of RPO.…”

Section: Rendezvous and Proximity Operationsmentioning

confidence: 99%

“…In comparison, solving Problem 65 directly can avoid virtual net construction altogether if an efficient solution method is available. To this end, the keep-out zone B(t) is usually chosen to be a polytope, an ellipsoid, or the union of a mix of both if multiple keep-out zones are considered (Hu et al, 2018). As shall be seen below, polytope approximation methods yield better optimality, while ellipsoidal methods yield better computational efficiency.…”

Section: Rendezvous and Proximity Operationsmentioning

confidence: 99%

Advances in Trajectory Optimization for Space Vehicle Control

Malyuta¹,

Yu²,

Elango³

et al. 2021

Preprint

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Space mission design places a premium on cost and operational efficiency. The search for new science and life beyond Earth calls for spacecraft that can deliver scientific payloads to geologically rich yet hazardous landing sites. At the same time, the last four decades of optimization research have put a suite of powerful optimization tools at the fingertips of the controls engineer. As we enter the new decade, optimization theory, algorithms, and software tooling have reached a critical mass to start seeing serious application in space vehicle guidance and control systems. This survey paper provides a detailed overview of recent advances, successes, and promising directions for optimization-based space vehicle control. The considered applications include planetary landing, rendezvous and proximity operations, small body landing, constrained attitude reorientation, endo-atmospheric flight including ascent and reentry, and orbit transfer and injection. The primary focus is on the last ten years of progress, which have seen a veritable rise in the number of applications using three core technologies: lossless convexification, sequential convex programming, and model predictive control. The reader will come away with a well-rounded understanding of the state-of-the-art in each space vehicle control application, and will be well positioned to tackle important current open problems using convex optimization as a core technology.

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“…For on-orbital servicing spacecrafts, autonomous rendezvous to target has attracted extensive research interests (Hu et al, 2018, 2019; Gao et al, 2009; Mancini et al, 2020, Yang, 2019). Several projects have been started to investigating safe and autonomous rendezvous problem such as the NASA’s DART program (Timothy, 2003) and the Phoenix mission (Gunn et al, 2015), and so forth.…”

Section: Introductionmentioning

confidence: 99%

Suboptimal obstacles avoidance control of spacecraft rendezvous

Cao¹,

Xiao

2020

Transactions of the Institute of Measurement and Control

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Spacecraft on-orbital services and docking require their autonomous rendezvous control system to have obstacle avoidance capability. Motivated by this, a suboptimal velocity artificial potential function-based control scheme is presented. An ellipsoid model is applied to describe the outer envelopes of the service spacecraft and the obstacles via an eigenvalue algorithm. This has better description precision than the traditional methods. The potential sigmoid function is used to generate repulsive force to avoid obstacles collision. A velocity artificial potential function-based controller is finally developed to ensure that the relative speed of the service spacecraft is reduced to zero before reaching the outer envelops of obstacles. The shaping parameters of the attractive potential function are adaptively optimized. Numerical simulations are performed to demonstrate that the approach can achieve a safe and autonomous rendezvous with fuel cost saved.

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Trajectory optimization for accompanying satellite obstacle avoidance

Cited by 27 publications

References 32 publications

Robust Finite-Time Control Algorithm Based on Dynamic Sliding Mode for Satellite Attitude Maneuver

Robust Finite-Time Control Algorithm Based on Dynamic Sliding Mode for Satellite Attitude Maneuver

Advances in Trajectory Optimization for Space Vehicle Control

Suboptimal obstacles avoidance control of spacecraft rendezvous

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