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Special Issue "Advanced Spacecraft Structural Dynamics and Actuation Control"

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A special issue of Actuators (ISSN 2076-0825). This special issue belongs to the section "Aircraft Actuators".

Deadline for manuscript submissions: 25 September 2023 | Viewed by 4360

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Special Issue Editors

Prof. Dr. Dengqing Cao

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Guest Editor

School of Astronautics, Harbin Institute of Technology, Harbin, China
Interests: spacecraft dynamics and control

Prof. Dr. Xiangying Guo
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Guest Editor

School of Mechanical and Electrical Engineering, Beijing University of Technology, Beijing, China
Interests: morphing structure design and dynamics

Dr. Shuai Chen

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Guest Editor

School of Astronautics, Harbin Institute of Technology, Harbin, China
Interests: spacecraft dynamics and control

Special Issue Information

Dear Colleagues,

Large-scale flexible spacecrafts (LSFS) represent important strategic space equipment for the future utilization of space resources, exploration of the universe, and long-term in-orbit residence. The coupling effect of attitude motion and structural vibration is very prominent for LSFS, and the study of the nonlinear coupling dynamic characteristics of attitude motion and structural vibration is an important scientific issue. The recent literature has provided a number of contributions associated with the dynamic modeling of such spacecraft, whilst the current ongoing research is devoted to nonlinear vibration and actuation control, addressing specific needs and issues. The aim of the present Special Issue is to collect original papers concerned with the dynamical modeling approach, nonlinear vibration analysis, actuation control design, and coordinated control of attitude motion and structural vibration for LSFS or its component structures. Theoretical, numerical and experimental contributions are all welcome, provided that they deal with the dynamics and control of flexible composite structures equipped on the LSFS. Modern analyses pertaining to active vibration suppression and attitude adjustment are particularly encouraged, providing both analytical and experimental results.

This topic is related to actuator control systems and their application in structural vibration suppression and attitude control of spacecrafts.

Prof. Dr. Dengqing Cao
Prof. Dr. Xiangying Guo
Dr. Shuai Chen
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Actuators is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 1800 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

flexible spacecraft
composite structures
dynamic modeling
nonlinear vibration
active vibration control
attitude maneuver
orbital maneuver
actuation control

Published Papers (6 papers)

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Research

Open AccessArticle

An Obstacle-Avoidance Motion Planning Method for Redundant Space Robot via Reinforcement Learning

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Actuators 2023, 12(2), 69; https://doi.org/10.3390/act12020069 - 08 Feb 2023

Viewed by 621

Abstract

On-orbit operation tasks require the space robot to work in an unstructured dynamic environment, where the end-effector’s trajectory and obstacle avoidance need to be guaranteed simultaneously. To ensure the completability and safety of the tasks, this paper proposes a new obstacle-avoidance motion planning method for redundant space robots via reinforcement learning (RL). First, the motion planning framework, which combines RL with the null-space motion for redundant space robots, is proposed according to the decomposition of joint motion. Second, the RL model for null-space obstacle avoidance is constructed, where the RL agent’s state and reward function are defined independent of the specific information of obstacles so that it can adapt to dynamic environmental changes. Finally, a curriculum learning-based training strategy for RL agents is designed to improve sample efficiency, training stability, and obstacle-avoidance performance. The simulation shows that the proposed method realizes reactive obstacle avoidance while maintaining the end-effector’s predetermined trajectory, as well as the adaptability to unstructured dynamic environments and robustness to the space robot’s dynamic parameters. Full article

(This article belongs to the Special Issue Advanced Spacecraft Structural Dynamics and Actuation Control)

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Open AccessArticle

Fractional Derivative Viscosity of ANCF Cable Element

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Actuators 2023, 12(2), 64; https://doi.org/10.3390/act12020064 - 02 Feb 2023

Cited by 1 | Viewed by 464

Abstract

Typical engineering cable structures, such as high-voltage wire and wire rope, usually bring a damping effect which cannot be ignored due to the technological problems of manufacturing. For such problems, especially the damping of cable structures undergoing large displacement and severe deformation, few studies have been reported in the past. In this work, the fractional derivative viscosity model is introduced into the cables described by the absolute nodal coordinate formulation. The computer implementation algorithm of the proposed cable damping model is given based on the three-parameter fractional derivative model. Two numerical examples demonstrate the effectiveness and convergence property of the proposed cable damping model. An experiment is proposed in which a wire is tensioned and released. Configurations are captured by the high-speed camera and compared with the results obtained from the numerical simulation. The agreement of the simulation and experimental results validates the proposed cable damping in application. Full article

(This article belongs to the Special Issue Advanced Spacecraft Structural Dynamics and Actuation Control)

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Open AccessArticle

Natural Characteristics Analysis for the Spacecraft Equipped with Constructed Cantilever Solar Panels

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Actuators 2023, 12(1), 3; https://doi.org/10.3390/act12010003 - 21 Dec 2022

Viewed by 571

Abstract

The power series polynomial constraining method is proposed in this paper. The dynamical model of the cantilever plate can be established by applying the constraint, which is different from the traditional polynomial. Firstly, the characteristic orthogonal polynomial was used to describe the displacement field of the rectangular plate of which all edges are free. Then the four-sided free plate was equivalent to cantilever plate by power series multiplier constraint method. The characteristic equation of the constructed cantilever plate was obtained by the Rayleigh–Ritz method. Natural frequencies and modal shapes of the plate were obtained by solving the characteristic equation. Next, the proposed method was adopted to establish dynamical model of a pair of solar panels clamped on the central platform symmetrically. The convergence of the proposed method was verified by comparing the calculated results of the cantilever plate with that of the finite element software ANSYS 15.0. The optimum order the power series polynomial was obtained by comparing different results. The analysis of the dynamical characteristics of the cantilever plate and the spacecraft demonstrates the validation of the proposed method. This method can provide a new idea for the plate with local edge constrained. Full article

(This article belongs to the Special Issue Advanced Spacecraft Structural Dynamics and Actuation Control)

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Open AccessArticle

Quantifying Uncertainties in Nonlinear Dynamics of a Modular Assembly Using the Resonance Decay Method

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Actuators 2022, 11(12), 350; https://doi.org/10.3390/act11120350 - 27 Nov 2022

Viewed by 671

Abstract

Modular assembling is a promising approach to constructing large spacecraft beyond the size limitations posed by launch vehicles. However, the uncertainties and nonlinearities of the dynamics associated with the assembled structure are deeply concerned with the design stage of such a spacecraft. Conventionally, this concern can be relieved by performing Ground Vibration Testing (GVT) of the structure. Nevertheless, it is challenging for a modular assembly, in which a very low-frequency behaviour and a lack of dynamic testing procedure that can incorporate nonlinearities are two major obstacles. In this regard, the present paper first introduces a demonstrator of Large Structure Assembly (LSA demonstrator), which includes a soft-bungee suspension system, a 6 m long modular assembly, a vibration control system, and a noncontact measurement system. Secondly, a new quantification procedure for the modular assembly, which utilises the resonance decay method, was proposed in this paper. Detailed test steps were illustrated through the demonstrator, in which the backbone curves were treated as key measurement targets in quantifying its nonlinear dynamics. The uncertainties in nonlinear dynamics were also evaluated by assembling and disassembling the structure multiple times. Results have shown that the proposed procedure can efficiently and accurately quantify the dynamics of a highly flexible, large-scale modular assembly. Full article

(This article belongs to the Special Issue Advanced Spacecraft Structural Dynamics and Actuation Control)

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Open AccessArticle

Investigations on Nonlinear Dynamic Modeling and Vibration Responses of T-Shaped Beam Structures

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Actuators 2022, 11(10), 293; https://doi.org/10.3390/act11100293 - 12 Oct 2022

Viewed by 648

Abstract

A novel nonlinear dynamic modeling approach is proposed for the T-shaped beam structures widely used in the field of aerospace. All of the geometrical nonlinearities including the terms in the deformation of the beams, the terms at the connections, and the free ends of beams are considered in the dynamic modeling process. The global mode method is employed to determine the natural frequencies and global mode shapes of the linearized system. The validity and accuracy of the derived model are verified by comparing the natural frequencies obtained with those calculated from FEM. Adopting the Galerkin truncation procedure, a set of reduced-order nonlinear ODEs is obtained for the structure. A study on the variation of dynamic responses taking the different numbers of global modes into account is performed to determine the number of modes taken in nonlinear vibration analysis. A comparison between the responses of the system with linear or nonlinear matching and boundary conditions is given to evaluate the importance of neglecting and reserving the nonlinear terms in matching and boundary conditions. It is shown that ignoring the nonlinear terms in both matching and boundary conditions may significantly alter the responses while developing the discretized governing ODEs of the structure. Full article

(This article belongs to the Special Issue Advanced Spacecraft Structural Dynamics and Actuation Control)

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Open AccessArticle

Shock-Induced Vibration of Composite Truss Core Sandwich Plates with Distributed Nonlinear Absorbers by Optimal Locations

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Actuators 2022, 11(8), 225; https://doi.org/10.3390/act11080225 - 06 Aug 2022

Viewed by 798

Abstract

In order to solve the problems of limited installation space and strict additional quality, the effects of internal distributed nonlinear energy sinks (NES) considering optimal locations on a composite truss core sandwich plate are investigated in this paper. Choose five NESs here and inset them in the different places of the sandwich plate to suppress the vibration of the plate, which is excited by a half-wave shock. The coupled dynamic equations of the system are derived by the principle of conservation of energy. Then, the vibration-control performances of five NESs are discussed by numerical simulation. The distributions of the five NESs are analyzed, and the optimal position distributions are obtained. Based on the optimal location, the transient responses of the system are studied. Moreover, the performances of five NESs and a single NES are compared in different dimensions. Finally, it is found that the selection of parameters has a great impact on the effectiveness of the five NESs. The new distribution way is introduced to improve the suppression effects of the five NESs in the sandwich plate. Full article

(This article belongs to the Special Issue Advanced Spacecraft Structural Dynamics and Actuation Control)

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Special Issue "Advanced Spacecraft Structural Dynamics and Actuation Control"

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