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Symmetry
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Symmetry in Spacecraft Guidance and Control: Theories and Applications
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Symmetry in Spacecraft Guidance and Control: Theories and Applications

A special issue of Symmetry (ISSN 2073-8994). This special issue belongs to the section "Engineering and Materials".

Deadline for manuscript submissions: closed (31 October 2023) | Viewed by 3988

Special Issue Editors

Dr. Chuang Liu

E-Mail Website
Guest Editor
School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China
Interests: attitude control; satellite swarm dynamics and control; multi-objective optimization control
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Dong Ye

E-Mail Website
Guest Editor
Research Center of Satellite Technology, Harbin Institute of Technology, Harbin 150001, China
Interests: spacecraft dynamics and control; space robot; guidance, navigation and control
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Haizhao Liang

E-Mail Website
Guest Editor
School of Aeronautics and Astronautics, Sun Yat-sen University, Shenzhen 510275, China
Interests: game theory; learning (artificial intelligence); missile guidance; optimal control; multi-agent systems
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

This Special Issue will include high-quality peer-reviewed articles on spacecraft dynamics, linear control, and nonlinear control, with an emphasis on robust high-precision control, as well as semi-physical experiment in attitude control. In this Special Issue, we welcome the submission of scientific articles on linear and nonlinear controller designs of spacecraft influenced by multiple symmetric or asymmetric disturbances, with the representations of Euler angles, quaternions, modified Rodrigues, etc. Authors are given the opportunity to publish research on the novel robust controller design applied in spacecraft control, on non-fragile controller design dealing with symmetric controller perturbations or actuator uncertainties, simulation of space vehicles cooperative strategies, as well as works solving engineering problems in intelligent guidance and control or focusing on novel guidance methods of space or near space vehicles and rigid and flexible spacecraft dynamics and control, including dynamics simulations and advanced controller design.

Dr. Chuang Liu
Prof. Dr. Dong Ye
Dr. Haizhao Liang
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. Symmetry 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

  • attitude control
  • spacecraft cluster topology
  • satellite swarm control
  • multi-objective optimization control
  • swarm game theory
  • hardware-in-a-loop simulation
  • non-fragile control
  • intelligent and bionic game
  • intelligent guidance and control

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

Published Papers (2 papers)

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Research

11 pages, 2153 KiB  
Article
Optimal Penetration Guidance Law for High-Speed Vehicles against an Interceptor with Modified Proportional Navigation Guidance
by Lei Feng, Wang Lu, Fenglin Wang, Fan Zhang and Qiangui Sun
Symmetry 2023, 15(7), 1337; https://doi.org/10.3390/sym15071337 - 30 Jun 2023
Viewed by 1093
Abstract
Aiming at the penetration problem of high-speed vehicles against a modified proportional guidance interceptor, a three-dimensional mathematical model of attack–defense confrontation between the high-speed vehicle and the interceptor is established in this paper. The modified proportional navigation guidance law of the interceptor is [...] Read more.
Aiming at the penetration problem of high-speed vehicles against a modified proportional guidance interceptor, a three-dimensional mathematical model of attack–defense confrontation between the high-speed vehicle and the interceptor is established in this paper. The modified proportional navigation guidance law of the interceptor is included in the model, and control constraints, pitch angle velocity constraints, and dynamic delay are introduced. Then, the performance index of the optimal penetration of high-speed vehicles is established. Under the condition of considering the 180-degree BTT control, the analytical solutions of the optimal speed roll angle and the optimal overload of high-speed vehicles are obtained according to symmetric Hamilton principle. The simulation results show that the overload switching times of high-speed vehicles to achieve optimal penetration are N − 1, where N is the modified proportional guidance coefficient of the interceptor. When the maximum speed roll angle velocity is [60, 90] degrees per second, the penetration effect of high-speed vehicles is good. Finally, the optimal penetration guidance law proposed in this paper can achieve a miss distance of more than 5 m when the overload capacity ratio is 0.33. Full article
(This article belongs to the Special Issue Symmetry in Spacecraft Guidance and Control: Theories and Applications)
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13 pages, 1028 KiB  
Article
The Optimal Deployment Strategy of Mega-Constellation Based on Markov Decision Process
by Xuefeng Wang, Shijie Zhang and Hongzhu Zhang
Symmetry 2023, 15(5), 1024; https://doi.org/10.3390/sym15051024 - 5 May 2023
Cited by 1 | Viewed by 1874
Abstract
LEO satellite mega-constellation projects have been proposed by many countries or commercial organizations in recent years. With more than 2000 satellites launched by SpaceX to configure the Starlink system, the orbital resources are more constrained given the existence of spacecrafts and countless orbital [...] Read more.
LEO satellite mega-constellation projects have been proposed by many countries or commercial organizations in recent years. With more than 2000 satellites launched by SpaceX to configure the Starlink system, the orbital resources are more constrained given the existence of spacecrafts and countless orbital debris. Due to this, the operating environment is full of uncertainty and information symmetry is absent for designers and stakeholders during the process of project deployment. The flux model of space debris on orbit has been built for assessing the LEO operation environment. Based on the orbital debris flux model, the collision probability can be calculated, which is an important variable of the state space. Given the condition that tge number of satellites decreases due to collision between satellites and debris, the Markov decision model has been built for optimal deployment strategy and decision-making. In order to assure that the mega-constellation system could provide services when satellites have failed, additional satellites need to be launched. The optimal deployment is the decision to launch a moderate number of satellites to maximize the benefit and minimize the cost. Assuming that at least 30 satellites need to be operated, 4 deployment scenarios are considered and the optimal deployment strategies can be obtained. Full article
(This article belongs to the Special Issue Symmetry in Spacecraft Guidance and Control: Theories and Applications)
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