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Aerospace
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Spacecraft Dynamics and Control (2nd Edition)
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Spacecraft Dynamics and Control (2nd Edition)

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Astronautics & Space Science".

Deadline for manuscript submissions: 31 December 2024 | Viewed by 4305

Special Issue Editor

Prof. Dr. Fanghua Jiang

E-Mail Website
Guest Editor
School of Aerospace Engineering, Tsinghua University, Beijing 100084, China
Interests: astrodynamics; orbit design and trajectory optimization for space exploration
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Spacecraft dynamics and control studies the orbit and attitude dynamics concerning the motion of spacecraft, including rockets, satellites, probes, space robots, etc., as well as their orbit and attitude determination and control. The dynamics and control for the orbit and attitude of spacecraft are fundamental to space missions both around the Earth and in deep space. Although the dynamics and control of spacecraft is a traditional topic, space missions continue to be innovated, new theories continue to emerge, and new technologies are continuously being combined.

This Special Issue mainly focuses on the advanced orbit and attitude dynamics and control of spacecraft. It is expected to include relevant new concepts, theories, models, methods, algorithms, techniques, discoveries, results, etc. Although disruptive theory and technology innovation should be rare, improving traditional methods or techniques to effectively solve new problems, solving technical challenges in new applications, proposing new ones to skillfully solve old problems, and finding new interesting results in ordinary problems are all encouraged. Authors are invited to submit full research and review articles on the dynamics and control of spacecraft concerning (but not limited to) the following fields: orbital design, trajectory optimization, orbit determination and prediction, attitude determination, control, and dynamics, guidance, navigation, and control of spacecraft, multi-target space exploration, satellite constellation, formation flying, solar sail, low-energy transfer in multi-body gravitational field, debris removal, Earth and space observation, asteroid flyby exploration and contact detection, space exploration sampling return, planetary system exploration, artificial intelligence, etc., all of which significantly challenge the astrodynamics.

Prof. Dr. Fanghua Jiang
Guest Editor

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. Aerospace 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

  • spacecraft control and dynamics
  • orbital design
  • trajectory optimization
  • attitude determination, control and dynamics
  • satellite constellation
  • formation flying
  • debris removal

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Related Special Issue

Published Papers (5 papers)

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Research

21 pages, 17699 KiB  
Article
Analytical Second-Order Extended Kalman Filter for Satellite Relative Orbit Estimation
by Zhen Yang, Mingyan Shang and Juqi Yin
Aerospace 2024, 11(11), 887; https://doi.org/10.3390/aerospace11110887 - 28 Oct 2024
Viewed by 499
Abstract
This study considers a relative orbit estimation problem wherein an observing spacecraft navigates with respect to a target space object at a large separation distance (several kilometers) using only the bearing angles obtained by a single onboard camera. Generally, the extended Kalman filter [...] Read more.
This study considers a relative orbit estimation problem wherein an observing spacecraft navigates with respect to a target space object at a large separation distance (several kilometers) using only the bearing angles obtained by a single onboard camera. Generally, the extended Kalman filter (EKF), which is based on linear relative motion equations such as the Clohessy–Wiltshire equation, is used for the relative navigation of satellites. The EKF linearizes the estimation error around the current estimate and applies the Kalman filter equations to this linearized system. However, it has been shown that nonlinearities of the orbit determination problem can make the linearization assumption insufficient to represent the actual uncertainty. Therefore, an analytical second-order extended Kalman filter (ASEKF) for relative orbit estimation is proposed in this study. The ASEKF, to sequentially estimate the relative states of satellites and their associated uncertainties, is formulated based on a second-order analytic relative-motion equation under J2-perturbtation, which can overcome the deficiencies of existing approaches that mainly focus on applications in two-body, near-circular, and linearized orbit dynamics. Numerical results show that the proposed method provides superior robustness and mean-square error performance compared to linear estimators under the conditions considered. Full article
(This article belongs to the Special Issue Spacecraft Dynamics and Control (2nd Edition))
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27 pages, 1576 KiB  
Article
Pose-Constrained Control of Proximity Maneuvering for Tracking and Observing Noncooperative Targets with Unknown Acceleration
by Mingyue Zheng, Yulin Zhang, Xun Wang and Li Fan
Aerospace 2024, 11(10), 828; https://doi.org/10.3390/aerospace11100828 - 9 Oct 2024
Viewed by 472
Abstract
This paper proposes a pose control scheme of for proximity maneuvering for tracking and observing noncooperative targets with unknown acceleration, which is an important prerequisite for on-orbit operations in space. It mainly consists of a finite-time extended state observer and constraint processing procedures. [...] Read more.
This paper proposes a pose control scheme of for proximity maneuvering for tracking and observing noncooperative targets with unknown acceleration, which is an important prerequisite for on-orbit operations in space. It mainly consists of a finite-time extended state observer and constraint processing procedures. Firstly, relative pose-coupled kinematics and dynamics models with unknown integrated disturbances are established based on dual quaternion representations. Then, a finite-time extended state observer is designed using the super-twisting algorithm to estimate the integrated disturbances. Both observation field of view and collision avoidance pose-constrained models are constructed to ensure that the service spacecraft continuously and safely observes the target during proximity maneuvering. And the constraint models are further incorporated into the design of artificial potential function with a unique minimum. After that, the proportional–derivative-like pose-constrained tracking control law is proposed based on the estimated disturbances and the gradient of the artificial potential function. Finally, the effectiveness of the control scheme is verified through numerical simulations. Full article
(This article belongs to the Special Issue Spacecraft Dynamics and Control (2nd Edition))
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14 pages, 3954 KiB  
Article
Test Method for Single Satellite’s Inter-Satellite Link Pointing and Tracking via Ground Station
by Zhenqiang Hong, Xuxing Huang, Lifeng Yang, Zhiqiang Bian, Yong Yang and Shuang Li
Aerospace 2024, 11(9), 713; https://doi.org/10.3390/aerospace11090713 - 31 Aug 2024
Viewed by 691
Abstract
An inter-satellite link is a key technology that improves control accuracy, transmission efficiency, and autonomous capability of constellations. A satellite’s pointing and tracking abilities mainly determine the inter-satellite link’s performance, which should be validated through an in-orbit test. However, during the construction of [...] Read more.
An inter-satellite link is a key technology that improves control accuracy, transmission efficiency, and autonomous capability of constellations. A satellite’s pointing and tracking abilities mainly determine the inter-satellite link’s performance, which should be validated through an in-orbit test. However, during the construction of the constellation, the distribution of satellites does not satisfy the constraints of establishing the inter-satellite link. A test method for inter-satellite link pointing and tracking is developed with respect to a single satellite. A practical mission scenario for testing inter-satellite links’ performance is constructed. A virtual satellite is introduced as the target satellite to establish an inter-satellite link with the local satellite. The orbit of the virtual target satellite between two ground stations is characterized based on the Newton–Raphson method. By comparing the predicted and actual time differences between two ground stations receiving the signals from the local satellite, the inter-satellite link pointing and tracking abilities are evaluated independently. Numerical simulations verify the design of the virtual satellite. The single satellite test method for inter-satellite link pointing and tracking abilities is available. Full article
(This article belongs to the Special Issue Spacecraft Dynamics and Control (2nd Edition))
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22 pages, 8726 KiB  
Article
Space-Based Passive Orbital Maneuver Detection Algorithm for High-Altitude Situational Awareness
by Shihang Yang, Xin Jin, Baichun Gong and Fei Han
Aerospace 2024, 11(7), 563; https://doi.org/10.3390/aerospace11070563 - 10 Jul 2024
Viewed by 1367
Abstract
Orbital maneuver detection for non-cooperative targets in space is a key task in space situational awareness. This study develops a passive maneuver detection algorithm using line-of-sight angles measured by a space-based optical sensor, especially for targets in high-altitude orbit. Emphasis is placed on [...] Read more.
Orbital maneuver detection for non-cooperative targets in space is a key task in space situational awareness. This study develops a passive maneuver detection algorithm using line-of-sight angles measured by a space-based optical sensor, especially for targets in high-altitude orbit. Emphasis is placed on constructing a new characterization for maneuvers as well as the corresponding detection method. First, the concept of relative angular momentum is introduced to characterize the orbital maneuver of the target quantitatively, and the sensitivity of the proposed characterization is analyzed mathematically. Second, a maneuver detection algorithm based on the new characterization is designed in which sliding windows and correlations are utilized to determine the mutation of the maneuver characterization. Subsequently, a numerical simulation system composed of error models, reference missions and trajectories, and computation models for estimating errors is established. Then, the proposed algorithm is verified through numerical simulations for both long-range and close-range targets. The results indicate that the proposed algorithm is effective. Additionally, the sensitivity of the proposed algorithm to the width of the sliding window, accuracy of the optical sensor, magnitude and number of maneuvers, and different relative orbit types is analyzed, and the sensitivity of the new characterization is verified using simulations. Full article
(This article belongs to the Special Issue Spacecraft Dynamics and Control (2nd Edition))
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26 pages, 14069 KiB  
Article
Trajectory Design of Potentially Hazardous Asteroid Exploration with Reusable Probes from Cislunar Space
by Chao Peng, Renyong Zhang and Yang Gao
Aerospace 2024, 11(7), 546; https://doi.org/10.3390/aerospace11070546 - 3 Jul 2024
Viewed by 818
Abstract
This article presents a trajectory design problem concerning the exploration of potentially hazardous near-Earth asteroids (PHAs) with reusable probes from cislunar space. A total of 20 probes, making round trips departing from and returning to a service space station in a lunar distant [...] Read more.
This article presents a trajectory design problem concerning the exploration of potentially hazardous near-Earth asteroids (PHAs) with reusable probes from cislunar space. A total of 20 probes, making round trips departing from and returning to a service space station in a lunar distant retrograde orbit, are expected to explore as many PHAs as possible by means of close flyby within a 10-year time window. The trajectory design problem was released in the 12th edition of China’s Trajectory Optimization Competition on 20 August 2022, and a total of 10 sets of trajectory solutions were submitted. As the authors who proposed the competition problem, we present in this article the problem descriptions, trajectory analysis, and design, as well as an impressive trajectory solution in which a total of 105 PHAs are explored. It is concluded that taking advantage of reusable probes from cislunar space is a promising option to efficiently explore large numbers of PHAs. Full article
(This article belongs to the Special Issue Spacecraft Dynamics and Control (2nd Edition))
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