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Aerospace
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Optimal Spacecraft Planning and Control
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Optimal Spacecraft Planning and Control

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

Deadline for manuscript submissions: closed (15 April 2023) | Viewed by 6107

Special Issue Editor

Prof. Dr. Igor Belokonov

E-Mail Website
Guest Editor
Department of Space Research, Samara State Aerospace University, Samara 443086, Russia
Interests: spacecraft; satellite; space exploration; space technology; orbital mechanics

Special Issue Information

Dear Colleagues,

We cordially welcome you to take part in a Special Issue pf Aerospace on " Optimal Spacecraft Planning and Control". 

Modern spacecraft always perform missions under conditions of strong restrictions on the available energy (both from the side of photovoltaic converters and from the side of the fuel reserves on board).

A variety of ways to control the trajectories and motion relative to the center of mass of spacecraft, due to the use of actuators, both traditional and novel (and their combinations), in some cases allows us to take a fresh look at solving traditional problems of motion control.

To date, a lot of theoretical and practical experience has been accumulated in the problems of optimal planning and control of the movement of spacecraft in the implementation of very complex missions, including interplanetary, near-planetary and on-planet missions.

Current developments in astronautics are characterized by increased accessibility to space for universities and small companies with a low available budget, which, on the one hand, certainly accelerates the pace of development of space technology but, on the other hand, creates new difficulties.

The current trend in the development of space technology is associated with the development of small spacecraft using commercial components, which dramatically reduces the cost of space missions. However, the low radiation resistance, the relatively low accuracy of the measuring devices and actuators used, and the small size of the spacecraft make it necessary to take into account new factors. For example, there are increased requirements for the accuracy of knowledge of the mass and centering characteristics of spacecraft and high sensitivity of the control results to the accuracy of knowing the mass and centering characteristics or ensuring their required values. In other words, the features of small-sized spacecraft created by universities using commercial components require the development of new approaches and methods for solving problems of optimal planning and motion control.

The presentation of new results in the choice of programs and control laws, optimal planning for solving navigation problems with departure trajectories to the moon and other planets, and the development of new methods of optimal control are welcome.

Undoubtedly, it is very important to disseminate the solutions to new problems of optimal control and their impact on new space missions. We are eagerly awaiting your original articles, including reviews.

Prof. Dr. Igor Belokonov
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.

Published Papers (4 papers)

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Research

13 pages, 3969 KiB  
Article
Disturbance Attenuation and Pointing Control System Design for an Improved Disturbance-Free Payload Spacecraft
by Ting Jin, Guohua Kang, Jian Cai, Shaoxia Jia, Jinghua Yang, Xinghua Zhang, Zhenhua Zhang, Long Li and Fangfang Liu
Aerospace 2023, 10(6), 530; https://doi.org/10.3390/aerospace10060530 - 02 Jun 2023
Viewed by 1037
Abstract
The low-frequency disturbances transmitted by flexible cables are difficult to be attenuated for a novel disturbance-free payload spacecraft, which decreases the payload’s pointing accuracy and stability. In this research, a new spacecraft configuration with a high-precision inertial reference unit composed of capacitive sensors [...] Read more.
The low-frequency disturbances transmitted by flexible cables are difficult to be attenuated for a novel disturbance-free payload spacecraft, which decreases the payload’s pointing accuracy and stability. In this research, a new spacecraft configuration with a high-precision inertial reference unit composed of capacitive sensors and a spherical test mass is proposed. The disturbance attenuation and pointing control system is subdivided into four interconnected control loops. The payload can be isolated from disturbances in the all-frequency band by the active vibration isolation control loop and the drag-free control loops, and its high-precision pointing requirement can be satisfied with the attitude pointing control loop and the attitude tracking control loop. An integrated control strategy is proposed, and the control system is decoupled into 12 single-input single-output control loops by pre-compensating, which lays the foundation for feedback design. Through the amplitude-frequency response analysis, the control bandwidth is designed according to the Proportional-Integral-Differentive control algorithm. The numerical simulations show that the disturbance attenuation performance is better than −20 dB in the all-frequency band, and the pointing accuracy and the pointing stability are better than 10−6 deg and 10−7 deg/s, respectively. The new spacecraft configuration and the disturbance attenuation and pointing control system provide a general technical solution for payloads with high-precision and high-stability requirements. Full article
(This article belongs to the Special Issue Optimal Spacecraft Planning and Control)
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16 pages, 1047 KiB  
Article
Quasioptimal Spacecraft Attitude Control Constructed According to the Poinsot Concept
by Yakov G. Sapunkov and Alexei V. Molodenkov
Aerospace 2023, 10(5), 402; https://doi.org/10.3390/aerospace10050402 - 26 Apr 2023
Viewed by 835
Abstract
The problem of attitude optimal control of a spacecraft as a solid body with the energy spent on maneuvering a spacecraft taken as a quadratic functional, and a fixed transition time, is investigated. The dynamic configuration of a spacecraft and boundary conditions on [...] Read more.
The problem of attitude optimal control of a spacecraft as a solid body with the energy spent on maneuvering a spacecraft taken as a quadratic functional, and a fixed transition time, is investigated. The dynamic configuration of a spacecraft and boundary conditions on an attitude and angular velocity are arbitrary; the control function is not limited. According to the Poinsot concept from theoretical mechanics on the interpretation of the angular motion of a solid body around a fixed point and with the help of the Pontryagin maximum principle, the quasioptimal analytical solution of the problem is obtained, which is brought to the algorithm. Numerical examples are provided that confirm the closeness of the quasioptimal solution to the optimal solution of the problem. Full article
(This article belongs to the Special Issue Optimal Spacecraft Planning and Control)
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20 pages, 3297 KiB  
Article
Studies of Satellite Position Measurements of LEO CubeSat to Identify the Motion Mode Relative to Its Center of Mass
by Igor Belokonov, Ivan Timbai and Petr Nikolaev
Aerospace 2023, 10(4), 378; https://doi.org/10.3390/aerospace10040378 - 18 Apr 2023
Viewed by 1330
Abstract
This paper addresses the possibility of reconstructing motion relative to the center of mass of a low Earth orbit (LEO) nanosatellite of the CubeSat 3U standard using satellite position measurements (Two-Line Element Set (TLE)). This kind of task needs to be performed in [...] Read more.
This paper addresses the possibility of reconstructing motion relative to the center of mass of a low Earth orbit (LEO) nanosatellite of the CubeSat 3U standard using satellite position measurements (Two-Line Element Set (TLE)). This kind of task needs to be performed in the case where it is not possible to establish radio communication with the nanosatellite after it is launched into orbit. Therefore, it is important for the nanosatellite developers to develop some understanding of what is going on with the nanosatellite in order to be able to analyze the current situation after deployment. The study was carried out on the example of the aerodynamically stabilized SamSat-218D nanosatellite developed by the professors and students of Samara National Research University. SamSat-218D was launched into a near-circular orbit with an average altitude of 486 km on April 2016 during the first launch campaign from the Vostochny cosmodrome. Knowledge of CubeSat aerodynamics allows estimating the nature of its possible motion relative to the CubeSat center of mass by ballistic coefficient changes, evaluated with the use of satellite position measurements. The analysis showed that SamSat-218D performed spatial rotation with an angular velocity of more than two degree per second and had not stabilized aerodynamically by 2 March 2022, when it entered the atmosphere and was destroyed. Full article
(This article belongs to the Special Issue Optimal Spacecraft Planning and Control)
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30 pages, 8742 KiB  
Article
Mission Design and Orbit-Attitude Control Algorithms Development of Multistatic SAR Satellites for Very-High-Resolution Stripmap Imaging
by Sangwon Lee, Sang-Young Park, Jeongbae Kim, Min-Ho Ka and Youngbum Song
Aerospace 2023, 10(1), 33; https://doi.org/10.3390/aerospace10010033 - 30 Dec 2022
Cited by 4 | Viewed by 1894
Abstract
This study designs a multistatic synthetic aperture radar (SAR) formation-flying system for very-high-resolution stripmap imaging (VHRSI) using manufacturable SAR microsatellites. Multistatic SAR formation specifications for VHRSI are derived based on the SAR image theory. For the simultaneous multi-satellite operation, the advantages of the [...] Read more.
This study designs a multistatic synthetic aperture radar (SAR) formation-flying system for very-high-resolution stripmap imaging (VHRSI) using manufacturable SAR microsatellites. Multistatic SAR formation specifications for VHRSI are derived based on the SAR image theory. For the simultaneous multi-satellite operation, the advantages of the autonomous orbit and attitude control are prominent in terms of the workload of the ground station or the efficient performance of missions. Therefore, the autonomous relative-orbit-control algorithm using relative orbital elements is developed to maintain the designed multistatic SAR formation. Additionally, an autonomous attitude-control algorithm for multistatic SAR imaging is designed by applying the optimal right-ascension of the descending node (RADN) sector concept. Finally, the resolution improvement of VHRSI is verified through multistatic SAR imaging simulations. The multistatic SAR formation is designed with three satellites separated by 7.5 km each in the along-track direction. Autonomous relative orbit control maintains the relative position error within 45 m (3σ). Additionally, the autonomous attitude control simulation verifies that the satellites perform attitude maneuvers suitable for the operation mode, and the pointing error is maintained within 0.0035° (3σ). The spatial resolution of the multistatic SAR system for VHRSI is 0.95 × 0.96 m, which satisfies the very-high-spatial-resolution requirement. Full article
(This article belongs to the Special Issue Optimal Spacecraft Planning and Control)
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