Attitude trajectory planning and attitude control for quad-rotor aircraft based on finite-time control technique

Cao

2022

Sensors

Aiming at the large-angle maneuver control problem of tracking spacecraft attitude in non-cooperative target rendezvous and proximity tasks, under the condition that the target spacecraft attitude information is unknown and the actuator output has physical limitations, a limited-time autonomous control method is proposed. First, an end-to-end pose estimation network is designed based on adaptive dual-channel feature extraction and dual attention. The information around the target is obtained through the adaptive dual-channel feature extraction module. The addition of spatial attention and channel attention allows the network to learn the target’s characteristics more accurately. Secondly, based on the improved adaptive update law, a finite-time saturation controller is designed using the hyperbolic tangent function and the auxiliary system. The hyperbolic tangent function can strictly ensure that the control torque of the control system is bounded. Finally, the simulation results show that the proposed autonomous control method can accurately estimate the attitude of the non-cooperative target spacecraft and can maneuver to the target attitude within 20 s under the condition that the actuator’s output is physically limited.

Section: Design Of a Finite-time Saturation Controllermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Autonomous Control of the Large-Angle Spacecraft Maneuvers in a Non-Cooperative Mission

Cao

2022

Sensors

Asian Journal of Control

“…It should be pointed out that most of the above results are studied the system's asymptotic stability. However, in a mass of practical applications, for instance, network systems [18,19], multi-agent systems [20], and aircraft systems [21,22], the state variable of the system should not exceed a given boundary value in a finite-time interval. In other words, these systems are required to exhibit finite-time stability (FTS).…”

Section: Introductionmentioning

confidence: 99%

A design proposal of finite‐time H_∞ controller for stochastic mean‐field systems

Liu,

Teng,

2024

A design proposal of finite‐time controller for stochastic mean‐field systems (MFSs), which are described by a Itô type differential equation, is presented in this paper. Firstly, based on control theory and finite‐time control theory, three sufficient conditions, which ensure the MFS satisfies stochastic finite‐time state feedback stabilization, are gained. Secondly, by decoupling correlation matrix inequalities, the state feedback controller (SFC) gains are obtained. Finally, the simulation results demonstrate that the large system of interacting particles can be approximated by MFS under certain conditions, and the controller design schemes proposed are feasible.

“…This control method dramatically improves the robustness of the system adaptability and flexibility, which has been used in many engineering tasks, such as earth observation distribution, aperture radar, gravity field measurement and so on [1]- [5]. At the same time, to meet the above requirements, the formation control technology for multiple spacecraft is also placing greater demands on the technology [6].…”

Section: Introductionmentioning

confidence: 99%

Formation Control of Spacecraft Based on SE(3) With Asymmetric Saturated Input

Li,

Peng,

Shang

et al. 2023

IEEE Access

In this paper, a set of integrated control problems for distributed spacecraft formation with input asymmetric constraints under external disturbances are studied. First, a new configuration error function is designed based on the compact nonlinear manifold SE(3), and the dynamic model of the coupling of the orbit and attitude of the distributed spacecraft formation is established. Then, in order to ensure the thrust constraints of the spacecraft in different directions, a novel asymmetric saturation controller is designed. Secondly, to deal with the effects of non-smooth asymmetric saturation, a continuously differentiable asymmetric saturation model is used based on a Gaussian error function. Using the proposed control scheme, the desired velocity can be tracked and the desired formation created. Finally, the finitetime stability of the spacecraft formation is demonstrated using Lyapunov's stability analysis, and the effectiveness of the proposed control scheme is verified by numerical simulation results.INDEX TERMS formation control; spacecraft; asymmetric saturated input; SE(3).