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Sensing and Modern Control Techniques for Aerospace Systems
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Sensing and Modern Control Techniques for Aerospace Systems

A special issue of Sensors (ISSN 1424-8220). This special issue belongs to the section "Intelligent Sensors".

Deadline for manuscript submissions: closed (20 November 2023) | Viewed by 2905

Special Issue Editors

Dr. Xiaolei Li

E-Mail Website
Guest Editor
Department of Control Science and Engineering, Harbin Institute of Technology, Harbin 150001, China
Interests: space tether system; fractional control system; sliding mode control and model predictive control
Prof. Dr. Guanghui Sun

E-Mail Website
Guest Editor
Department of Control Science and Engineering, Harbin Institute of Technology, Harbin 150001, China
Interests: visual servo control system; spacecraft dynamics and control; sliding mode control
Dr. Ganghui Shen

E-Mail Website
Guest Editor
School of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China
Interests: tethered spacecraft control; sliding mode control and constrained control

Special Issue Information

Dear Colleagues,

With the rapid development of aerospace engineering, in recent years, aerospace systems have gradually become large-scale and integrated. This change has led to the emergence of various aerospace technologies and systems, as well as new challenges in the sensing and modern control of aerospace systems. Various practical issues, such as measurement, sensing, and communication of large-scale structures, vibration suppression of flexible structures, complex dynamics and control of multi-body structures, distributed control and robust requirements, etc., are awaiting novel ideas and methods for their addressal. In aerospace system applications, the techniques of sensing and modern control need to deal with multi-input-multi-output, high nonlinearity, strong coupling, and uncertainties, which have always been topics of significant interest.

This Special Issue aims to collate original research and review articles on recent advances, technologies, solutions, applications, and new challenges in the field of sensing and modern control for aerospace systems. Application areas of interest include space exploration, space geodesy, high-accuracy sensing, space communications, spacecraft dynamics, advanced decision, robust control methods, etc.

Potential topics include, but are not limited to, the following:

  • Piezoelectric sensor–actuator and advanced sensors;
  • Dynamic vibration absorption and vibration suppression;
  • Space communication, signal processing and navigation;
  • Modeling and analysis of space multi-body dynamics;
  • Tethered satellite and space tethered robotic systems;
  • Space teleoperated technologies and telerobotic systems;
  • Active disturbance rejection control for aerospace systems;
  • Fault diagnosis and fault-tolerant control for aerospace systems;
  • Deep learning and reinforcement learning for aerospace systems;
  • Advanced decision and robust control for aerospace systems.

We look forward to receiving your contributions.

Dr. Xiaolei Li
Prof. Dr. Guanghui Sun
Dr. Ganghui Shen
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. Sensors is an international peer-reviewed open access semimonthly 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 2600 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

  • aerospace systems
  • sensing technologies
  • modern control
  • fault diagnosis
  • vibration suppression
  • task decision and planning

Published Papers (3 papers)

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Research

12 pages, 3484 KiB  
Article
Mechanical Properties and Fatigue Life Analysis of Motion Cables in Sensors under Cyclic Loading
by Weizhe Liang, Wei Guan, Ying Ding, Chunjin Hang, Yan Zhou, Xiaojing Zou and Shenghai Yue
Sensors 2024, 24(4), 1109; https://doi.org/10.3390/s24041109 - 8 Feb 2024
Viewed by 567
Abstract
Motion cables, which are widely used in aero-engine sensors, are critical components that determine sensor stability. Because motion cables have unique motion characteristics, the study of their mechanical properties and reliability is very important. In addition, motion cables are complex in structure and [...] Read more.
Motion cables, which are widely used in aero-engine sensors, are critical components that determine sensor stability. Because motion cables have unique motion characteristics, the study of their mechanical properties and reliability is very important. In addition, motion cables are complex in structure and cannot be applied to conventional fixed cable research methods. In this study, a new approach is proposed to introduce the theory of anisotropic composites into a simplified cable model, so that the cable is both physically conditioned and has good mechanical properties. While applying the theory of anisotropic composites, the forces of tension and torsion are considered in a motion cable under the combined action. In this context, the reliability of the structure is the fatigue life of the cable. In this paper, the mechanical properties and fatigue life of motion cables are investigated using the finite element method at different inclination angles and fixation points. The simulation results show that there is a positive correlation between the inclination angle and the extreme stress in the motion cables, and the optimal inclination angle of 0° is determined. The number of fixing points should be reduced to minimize the additional moments generated during the movement and to ensure proper movement of the cables. The optimal configuration is a 0° inclination angle and two fixing points. Subsequently, the fatigue life under these optimal conditions is analyzed. The results show that the high-stress zone corresponds to the location of the short-fatigue life, which is the middle of the motion cables. Therefore, minimizing the inclination angle and the number of fixing points of the motion cables may increase their fatigue life and thus provide recommendations for optimizing their reliability. Full article
(This article belongs to the Special Issue Sensing and Modern Control Techniques for Aerospace Systems)
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17 pages, 1199 KiB  
Article
Temperature Compensation of Wind Tunnel Balance Signal Detection System Based on IGWO-ELM
by Xiang Dong, Hu Xu, Huibin Cao, Tao Cui and Yuxiang Sun
Sensors 2023, 23(16), 7224; https://doi.org/10.3390/s23167224 - 17 Aug 2023
Cited by 1 | Viewed by 791
Abstract
The wind tunnel balance signal detection system is widely employed in aerospace applications for the accurate and automated measurement of aerodynamic forces and moments. However, measurement errors arise under different environmental temperature. This paper addresses the issue of measurement accuracy under different temperature [...] Read more.
The wind tunnel balance signal detection system is widely employed in aerospace applications for the accurate and automated measurement of aerodynamic forces and moments. However, measurement errors arise under different environmental temperature. This paper addresses the issue of measurement accuracy under different temperature conditions by proposing a temperature compensation method based on an improved gray wolf optimization (IGWO) algorithm and optimized extreme learning machine (ELM). The IGWO algorithm is enhanced by improving the initial population position, convergence factor, and iteration weights of the gray wolf optimization algorithm. Subsequently, the IGWO algorithm is employed to determine the optimal network parameters for the ELM. The calibration decoupling experiment and high-low temperature experiment are designed and carried out. On this basis, ELM, GWO-ELM, PSO-ELM, GWO-RBFNN and IGWO-ELM are used for temperature compensation experiments. The experimental results show that IGWO-ELM has a good temperature compensation effect, reducing the measurement error from 20%FS to within 0.04%FS. Consequently, the accuracy and stability of the wind tunnel balance signal detection system under different temperature environments are enhanced. Full article
(This article belongs to the Special Issue Sensing and Modern Control Techniques for Aerospace Systems)
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18 pages, 2105 KiB  
Article
A Novel Closed-Loop Structure for Drag-Free Control Systems with ESKF and LQR
by Xiaorong Ye, Junxiang Lian, Guoying Zhao and Dexuan Zhang
Sensors 2023, 23(15), 6766; https://doi.org/10.3390/s23156766 - 28 Jul 2023
Cited by 1 | Viewed by 951
Abstract
Space-borne gravitational wave detection satellite confronts many uncertain perturbations, such as solar pressure, dilute atmospheric drag, etc. To realize an ultra-static and ultra-stable inertial benchmark achieved by a test-mass (TM) being free to move inside a spacecraft (S/C), the drag-free control system of [...] Read more.
Space-borne gravitational wave detection satellite confronts many uncertain perturbations, such as solar pressure, dilute atmospheric drag, etc. To realize an ultra-static and ultra-stable inertial benchmark achieved by a test-mass (TM) being free to move inside a spacecraft (S/C), the drag-free control system of S/C requires super high steady-state accuracies and dynamic performances. The Active Disturbance Rejection Control (ADRC) technique has a certain capability in solving problems with common perturbations, while there is still room for optimization in dealing with the complicated drag-free control problem. When faced with complex noises, the steady-state accuracy of the traditional control method is not good enough and the convergence speed of regulating process is not fast enough. In this paper, the optimized Active Disturbance Rejection Control technique is applied. With the extended state Kalman filter (ESKF) estimating the states and disturbances in real time, a novel closed-loop control structure is designed by combining the linear quadratic regulator (LQR) and ESKF, which can satisfy the design targets competently. The comparative analysis and simulation results show that the LQR controller designed in this paper has a faster response and a higher accuracy compared with the traditional nonlinear state error feedback (NSEF), which uses a deformation of weighting components of classical PID. The new drag-free control structure proposed in the paper can be used in future gravitational wave detection satellites. Full article
(This article belongs to the Special Issue Sensing and Modern Control Techniques for Aerospace Systems)
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