Search for Articles:
Title / Keyword
Author / Affiliation / Email
Journal
Article Type
 
 
Advanced Search
 
Section
Special Issue
Volume
Issue
Number
Page
 
3.9
2.2
Journals
Actuators
Special Issues
Advanced Spacecraft Structural Dynamics and Actuation Control
share announcement

Advanced Spacecraft Structural Dynamics and Actuation Control

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

Deadline for manuscript submissions: closed (31 May 2024) | Viewed by 24831

Special Issue Editors

Prof. Dr. Dengqing Cao

E-Mail Website
Guest Editor
School of Astronautics, Harbin Institute of Technology, Harbin, China
Interests: spacecraft dynamics and control
Prof. Dr. Xiangying Guo

E-Mail Website
Guest Editor
School of Mechanical and Electrical Engineering, Beijing University of Technology, Beijing, China
Interests: morphing structure design and dynamics
Dr. Shuai Chen

E-Mail
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 2400 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

Benefits of Publishing in a Special Issue

  • Ease of navigation: Grouping papers by topic helps scholars navigate broad scope journals more efficiently.
  • Greater discoverability: Special Issues support the reach and impact of scientific research. Articles in Special Issues are more discoverable and cited more frequently.
  • Expansion of research network: Special Issues facilitate connections among authors, fostering scientific collaborations.
  • External promotion: Articles in Special Issues are often promoted through the journal's social media, increasing their visibility.
  • Reprint: MDPI Books provides the opportunity to republish successful Special Issues in book format, both online and in print.

Further information on MDPI's Special Issue policies can be found here.

Published Papers (10 papers)

Download All Papers
Order results
Result details
Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:

Research

22 pages, 27396 KiB  
Article
Mechanical Property Degradation of Entangled Metallic Wire Materials under Vibration Environment: Experiments and Prediction Models
by Yanhong Ma, Tianyu Liang, Yongfeng Wang, Zhizhou Wang and Jie Hong
Actuators 2023, 12(11), 418; https://doi.org/10.3390/act12110418 - 8 Nov 2023
Cited by 2 | Viewed by 1795
Abstract
Entangled metallic wire material (EMWM) can be utilized as a novel elastic element in vibration isolation devices for mechanical actuators. This paper presents a vibration experiment aimed at investigating the degradation behavior of mechanical performance in EMWM under a cyclic compressive environment. An [...] Read more.
Entangled metallic wire material (EMWM) can be utilized as a novel elastic element in vibration isolation devices for mechanical actuators. This paper presents a vibration experiment aimed at investigating the degradation behavior of mechanical performance in EMWM under a cyclic compressive environment. An electric vibration testing system, coupled with an isolation structure, is employed to apply compressive loads to the EMWM specimens. Through visual observations and quasi-static compression tests, the variations in geometric morphology and mechanical properties are studied, considering different relative densities and vibrational stress amplitudes. The results indicate a significant reduction in the compressed dimension of the specimens as the number of cycles increases, without any wire fractures or wear. The mechanical properties exhibit an increasing secant modulus and a decreasing loss factor. These variations ultimately lead to a gradual deviation of the vibration characteristics of the isolation structure from its design state, including resonance frequency and transmission rate. To forecast the mechanical property degradation of EMWM, prediction models are proposed, incorporating its dimensions, modulus, and damping by fitting the experiment results. This research provides valuable experimental data and presents an effective method to determine the operational lifespan of vibration isolators utilizing EMWM. Full article
(This article belongs to the Special Issue Advanced Spacecraft Structural Dynamics and Actuation Control)
►▼ Show Figures

Figure 1

17 pages, 3386 KiB  
Article
A Tangent Release Manipulation Controlled by a Dual-Arm Space Robot
by Xiaoyi Wang and Jayantha Katupitiya
Actuators 2023, 12(8), 325; https://doi.org/10.3390/act12080325 - 14 Aug 2023
Cited by 3 | Viewed by 2164
Abstract
As people further develop space with advanced technology, space robots have played a significant role in on-orbit servicing missions. Space robots can carry out more risky and complicated missions with less cost than astronauts. Dual-arm space robots can perform complex on-orbit space missions [...] Read more.
As people further develop space with advanced technology, space robots have played a significant role in on-orbit servicing missions. Space robots can carry out more risky and complicated missions with less cost than astronauts. Dual-arm space robots can perform complex on-orbit space missions more effectively than single-arm space robots. Since the coupled dynamics between the free-floating base and the arms exist in space robots, accurate coordinate control of the base and the arms is essential. Spacecraft release missions have been proposed to berth/deberth a spacecraft to a space station. Based on the existing release missions, a tangent release strategy is introduced in this paper, which can release a space object in the tangent direction of the final link of a space manipulator. This strategy can control a dual-arm space robot to deploy cargo/spacecraft in variable directions in 3D space without thrusters and the associated fuel consumption. For instance, this tangent release operation can transport cargo or modules of large-scale spacecraft needing on-orbit assembly. Considering model uncertainties, robust controllers again model uncertainties that are used to control the dual-arm space robot with high accuracy. Hence, a robust sliding mode controller (SMC) is utilized to accurately control the space robot to carry out the proposed tangent release strategy. For comparison, we select a conventional computed torque control (CTC) implemented by a PD-type controller. In the simulations, the SMC performs better in tracking accuracy and robustness against the model uncertainties than the PD controller. Numerical simulations indicate the feasibility and effectiveness of the tangent release manipulation of a space object by a dual-arm space robot. Full article
(This article belongs to the Special Issue Advanced Spacecraft Structural Dynamics and Actuation Control)
►▼ Show Figures

Figure 1

15 pages, 7203 KiB  
Article
Dynamic Modeling and Analysis of Spacecraft with Multiple Large Flexible Structures
by Jin Wei, Wei Liu, Jia Liu and Tao Yu
Actuators 2023, 12(7), 286; https://doi.org/10.3390/act12070286 - 13 Jul 2023
Cited by 2 | Viewed by 2116
Abstract
An analytical dynamic model is presented for a spacecraft with multiple large flexible structures. Based on the partial differential equations (PDEs) of the motion of the solar panel and deployable arm, the governing equations of the main-body and deployable antenna and the boundary [...] Read more.
An analytical dynamic model is presented for a spacecraft with multiple large flexible structures. Based on the partial differential equations (PDEs) of the motion of the solar panel and deployable arm, the governing equations of the main-body and deployable antenna and the boundary conditions at each end point are used to obtain the frequency and mode shapes of the system. Then, the ordinary differential equations (ODEs) of the system can be obtained from the orthogonality relations and mode shape. The influence of the deployable antenna on the frequencies and mode shapes of the spacecraft is investigated. The frequency veering and mode interchanged phenomenon are observed with the variation of the diameter of the deployable antenna. Using the ODEs, the dynamic responses of the spacecraft are calculated to study the influence of the control torque on the attitude and position of the antenna in the attitude maneuver. Full article
(This article belongs to the Special Issue Advanced Spacecraft Structural Dynamics and Actuation Control)
►▼ Show Figures

Figure 1

27 pages, 6338 KiB  
Article
Dynamic Modeling and Attitude–Vibration Cooperative Control for a Large-Scale Flexible Spacecraft
by Guiqin He and Dengqing Cao
Actuators 2023, 12(4), 167; https://doi.org/10.3390/act12040167 - 6 Apr 2023
Cited by 11 | Viewed by 3206
Abstract
Modern spacecraft usually have larger and more flexible appendages whose vibration becomes more and more prominent, and it has a great influence on the precision of spacecraft attitude. Therefore, the cooperative control of attitude maneuvering and structural vibration of the system has become [...] Read more.
Modern spacecraft usually have larger and more flexible appendages whose vibration becomes more and more prominent, and it has a great influence on the precision of spacecraft attitude. Therefore, the cooperative control of attitude maneuvering and structural vibration of the system has become a significant issue in the spacecraft design process. We developed a low-dimensional and high-precision mathematical model for a large-scale flexible spacecraft (LSFS) equipped with a pair of hinged solar arrays in this paper. The analytic global modes are used to obtain the rigid–flexible coupling discrete dynamic model, and the governing equations with multiple DOFs for the system are derived by using the Hamiltonian principle. The rigid–flexible coupled oscillating responses of LSFS under the three-axis attitude-driving torque pulse during the in-orbit attitude maneuvering process are investigated. A study on the flexibility of the hinge was also conducted. Based on the simplified and accurate dynamic model of the system, we can obtain a state-space model for LSFS conveniently, and the cooperative control schemes for rigid motion and flexible oscillation control are designed by using the LQR, PD, and PD + IS algorithms. The simulation results show that three cooperative controllers can realize spacecraft attitude adjustment and synchronously eliminate flexible oscillation successfully. By comparison, the PD + IS controller is simpler so that it is suitable for the real-time attitude–vibration cooperative control of spacecraft. Full article
(This article belongs to the Special Issue Advanced Spacecraft Structural Dynamics and Actuation Control)
►▼ Show Figures

Figure 1

23 pages, 1739 KiB  
Article
An Obstacle-Avoidance Motion Planning Method for Redundant Space Robot via Reinforcement Learning
by Zeyuan Huang, Gang Chen, Yue Shen, Ruiquan Wang, Chuankai Liu and Long Zhang
Actuators 2023, 12(2), 69; https://doi.org/10.3390/act12020069 - 8 Feb 2023
Cited by 8 | Viewed by 3529
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 [...] Read more.
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)
►▼ Show Figures

Figure 1

15 pages, 10358 KiB  
Article
Fractional Derivative Viscosity of ANCF Cable Element
by Yaqi Gu, Zuqing Yu, Peng Lan and Nianli Lu
Actuators 2023, 12(2), 64; https://doi.org/10.3390/act12020064 - 2 Feb 2023
Cited by 5 | Viewed by 2174
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 [...] Read more.
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)
►▼ Show Figures

Figure 1

19 pages, 9506 KiB  
Article
Natural Characteristics Analysis for the Spacecraft Equipped with Constructed Cantilever Solar Panels
by Yuteng Cao, Xudong Zhang, Dengqing Cao and Yuxin Hao
Actuators 2023, 12(1), 3; https://doi.org/10.3390/act12010003 - 21 Dec 2022
Cited by 3 | Viewed by 1921
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 [...] Read more.
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)
►▼ Show Figures

Figure 1

17 pages, 4412 KiB  
Article
Quantifying Uncertainties in Nonlinear Dynamics of a Modular Assembly Using the Resonance Decay Method
by Chengrong Lin, Ziheng Zhao, Zhenyu Wang, Jianping Jiang, Zhigang Wu and Xing Wang
Actuators 2022, 11(12), 350; https://doi.org/10.3390/act11120350 - 27 Nov 2022
Cited by 3 | Viewed by 2116
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, [...] Read more.
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)
►▼ Show Figures

Figure 1

19 pages, 3143 KiB  
Article
Investigations on Nonlinear Dynamic Modeling and Vibration Responses of T-Shaped Beam Structures
by Shuai Chen, Dengqing Cao, Jin Wei, Guiqin He, Bo Fang and Youxia Li
Actuators 2022, 11(10), 293; https://doi.org/10.3390/act11100293 - 12 Oct 2022
Cited by 1 | Viewed by 2073
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 [...] Read more.
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)
►▼ Show Figures

Figure 1

20 pages, 16501 KiB  
Article
Shock-Induced Vibration of Composite Truss Core Sandwich Plates with Distributed Nonlinear Absorbers by Optimal Locations
by Wei Zhang, Weixing Zhang, Zhong Luo, Jianen Chen and Xiangying Guo
Actuators 2022, 11(8), 225; https://doi.org/10.3390/act11080225 - 6 Aug 2022
Cited by 2 | Viewed by 2045
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 [...] Read more.
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)
►▼ Show Figures

Figure 1

Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:
 
Displaying articles 1-10
Back to TopTop