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Aerospace
Special Issues
Spacecraft Orbit Transfers
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Spacecraft Orbit Transfers

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 5542

Special Issue Editor

Dr. Zhenbo Wang

E-Mail Website
Guest Editor
Department of Mechanical, Aerospace and Biomedical Engineering, University of Tennessee, Knoxville, TN 37996, USA
Interests: optimal control; convex optimization; machine learning; guidance, navigation, and control; space systems; aerial vehicles; connected vehicles

Special Issue Information

Dear Colleagues,

Orbit transfers are a type of maneuver used by spacecraft to transition from one orbit to another. Recent advances in propulsion technologies and computational intelligence have enabled more efficient, low-cost, autonomous orbit transfers for a variety of complex space missions. For example, new propulsion systems can achieve very high specific impulses while enabling very low thrust levels for more efficient fuel consumption and extended periods during orbit transfers. Meanwhile, the rapid development of machine learning and computational guidance, navigation, and control approaches has provided significant opportunities to enable novel orbit transfer concepts with higher levels of autonomy and robustness in uncertain and disturbing mission environments.

The Special Issue aims to address the broad topics and advances in spacecraft orbit transfers and welcomes research articles and review papers in areas including, but not limited to, the following:

  • Earth–orbit transfers;
  • Interplanetary trajectories;
  • Low-thrust orbit transfers;
  • Rendezvous and proximity operations;
  • Orbit transfers for on-orbit servicing;
  • Orbit transfers of small satellites;
  • Ballistic lunar transfers;
  • Gravity-assist maneuvers;
  • Aerocapture, aerobraking, and atmospheric entry;
  • Aero-gravity assist maneuvers;
  • Advanced guidance, navigation, and control for orbit transfers;
  • Advanced propulsion technologies for orbit transfers;
  • Machine learning techniques for orbit transfers;
  • Advanced trajectory optimization methods for orbit transfers;
  • Launch trajectories and orbit insertion;
  • Orbit transfers for spacecraft formation flying.

Dr. Zhenbo Wang
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

  • orbit transfers
  • space propulsion
  • space trajectory
  • trajectory optimization
  • guidance, navigation, and control
  • interplanetary missions

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Published Papers (6 papers)

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Research

26 pages, 8614 KiB  
Article
A Low Earth Orbit Satellite-Orbit Extrapolation Method Based on Multi-Satellite Ephemeris Coordination and Multi-Stream Fractional Autoregressive Integrated Moving Average
by Wenliang Lin, Jian Yi, Tong Wang, Ke Wang, Zexi Huang, Zhongliang Deng, Yang Liu, Yicheng Liao, Heng Kang, Zeyang Liu and Junyu Zhang
Aerospace 2024, 11(9), 746; https://doi.org/10.3390/aerospace11090746 - 11 Sep 2024
Viewed by 321
Abstract
The low Earth orbit (LEO) satellite internet network (LEO-SIN) has become a heated issue for the next generation of mobile communications, serving as a crucial means to achieve global wide-area broadband coverage and, especially, mobile phone directly to satellite cell (MPDTSC) communication. The [...] Read more.
The low Earth orbit (LEO) satellite internet network (LEO-SIN) has become a heated issue for the next generation of mobile communications, serving as a crucial means to achieve global wide-area broadband coverage and, especially, mobile phone directly to satellite cell (MPDTSC) communication. The ultra-high-speed movement of LEO satellites relative to the Earth results in serious Doppler effects, leading to signal de-synchronization at the user end (UE), and relative high-speed motion leading to frequent satellite handovers. Satellite ephemeris, which indicates the satellite’s position, has the potential to determine the position of the transmit (Tx) within the LEO-SIN, thereby enhancing the reliability and efficiency of satellite communication. The adoption of ephemeris in the LEO-SIN has met some new challenges: (1) how UEs can acquire ephemerides before signal synchronization is complete, (2) how to minimize the frequency of ephemeris broadcasting, and (3) how to decrease the overhead of ephemeris broadcasting. To address the above challenges, this paper proposes a method for extrapolating the LEO-SIN orbit based on multi-satellite ephemeris coordination (MSEC) and the multi-stream fractional autoregressive integrated moving average (MS-FARIMA). First, a multi-factor global error analysis model for ephemeris-extrapolation error is established, which decomposes it into three types; namely, random error (RE), trending error (TE), and periodic error (PE), with a focus on increasing the extrapolation accuracy by improving RE and TE. Second, RE is eliminated by utilizing the ephemerides from multiple satellites received at the same UE at the same time, as well as multiple ephemerides from the same satellite at different times. Subsequently, we propose a new FARIMA algorithm with the innovation of a multi-stream data time-series forecast (TSF), which effectively improves ephemeris extrapolation errors. Finally, the simulation results show that the proposed method reduces ephemeris extrapolation errors by 33.5% compared to existing methods, which also contributes to a performance enhancement in the Doppler frequency offset (DFO) estimation of MPDTSC. Full article
(This article belongs to the Special Issue Spacecraft Orbit Transfers)
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20 pages, 5794 KiB  
Article
Optimal Impulsive Orbit Transfers from Gateway to Low Lunar Orbit
by Dario Sanna, Edoardo Maria Leonardi, Giulio De Angelis and Mauro Pontani
Aerospace 2024, 11(6), 460; https://doi.org/10.3390/aerospace11060460 - 7 Jun 2024
Cited by 1 | Viewed by 711
Abstract
Gateway represents a key element of the Artemis program for the upcoming lunar exploration aimed at establishing a sustainable presence by the mid-2030s. This paper investigates minimum-fuel bi-impulsive orbit transfers from Gateway to low lunar orbits (LLOs) with a maximum time of flight [...] Read more.
Gateway represents a key element of the Artemis program for the upcoming lunar exploration aimed at establishing a sustainable presence by the mid-2030s. This paper investigates minimum-fuel bi-impulsive orbit transfers from Gateway to low lunar orbits (LLOs) with a maximum time of flight of 48 h. Two distinct scenarios are analyzed: (i) target orbits with free right ascension of the ascending node (RAAN), and (ii) target orbits with specified RAAN. For case (i), a global optimization technique based on a heuristic algorithm is exploited to obtain the minimum-fuel transfer. Several inclinations of the target orbit are considered. For case (ii), two distinct techniques are proposed: (a) a purely heuristic approach, and (b) a semi-analytical method based on local refinement of a Lambert-based solution. Numerical propagations are conducted in all scenarios in a high-fidelity framework that includes all relevant perturbations. A comparison between the different strategies and the related numerical results is provided. Full article
(This article belongs to the Special Issue Spacecraft Orbit Transfers)
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16 pages, 4389 KiB  
Article
Solar Sail Optimal Performance in Heliocentric Nodal Flyby Missions
by Giovanni Mengali, Marco Bassetto and Alessandro A. Quarta
Aerospace 2024, 11(6), 427; https://doi.org/10.3390/aerospace11060427 - 24 May 2024
Viewed by 638
Abstract
Solar sails are propellantless propulsion systems that extract momentum from solar radiation pressure. They consist of a large ultrathin membrane, typically aluminized, that reflects incident photons from the Sun to generate thrust for space navigation. The purpose of this study is to investigate [...] Read more.
Solar sails are propellantless propulsion systems that extract momentum from solar radiation pressure. They consist of a large ultrathin membrane, typically aluminized, that reflects incident photons from the Sun to generate thrust for space navigation. The purpose of this study is to investigate the optimal performance of a solar sail-based spacecraft in performing two-dimensional heliocentric transfers to inertial points on the ecliptic that lie within an assigned annular region centered in the Sun. Similar to ESA’s Comet Interceptor mission, this type of transfer concept could prove useful for intercepting a potential celestial body, such as a long-period comet, that is passing close to Earth’s orbit. Specifically, it is assumed that the solar sail transfer occurs entirely in the ecliptic plane and, in analogy with recent studies, the flyby points explored are between 0.85au and 1.35au from the Sun. The heliocentric dynamics of the solar sail is described using the classical two-body model, assuming the spacecraft starts from Earth orbit (assumed circular), and an ideal force model to express the sail thrust vector. Finally, no constraint is imposed on the arrival velocity at flyby. Numerical simulation results show that solar sails are an attractive option to realize these specific heliocentric transfers. Full article
(This article belongs to the Special Issue Spacecraft Orbit Transfers)
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21 pages, 3696 KiB  
Article
Exploration and Maintenance of Homeomorphic Orbit Revs in the Elliptic Restricted Three-Body Problem
by Kevin I. Alvarado and Sandeep K. Singh
Aerospace 2024, 11(5), 407; https://doi.org/10.3390/aerospace11050407 - 17 May 2024
Cited by 2 | Viewed by 916
Abstract
A novel station-keeping strategy leveraging periodic revolutions of homeomorphic orbits in the Elliptic Restricted Three-Body Problem within the pulsating frame is presented. A systemic approach founded on arc-length continuation is presented for the discovery, computation, and classification of periodic revolutions that morph from [...] Read more.
A novel station-keeping strategy leveraging periodic revolutions of homeomorphic orbits in the Elliptic Restricted Three-Body Problem within the pulsating frame is presented. A systemic approach founded on arc-length continuation is presented for the discovery, computation, and classification of periodic revolutions that morph from their traditional circular restricted three-body counterparts to build an a priori dataset. The dataset is comprehensive in covering all possible geometric architectures of the restricted problem. Shape similarity is quantified using Hausdorff distance and works as a filter for the station-keeping algorithm in relation to appropriate target conditions. Finally, an efficient scheme to quantify impulsive orbit maintenance maneuvers that minimize the total fuel cost is presented. The proposed approach is salient in its generic applicability across any elliptic three-body system and any periodic orbit family. Finally, average annual station-keeping costs using the described methodology are quantified for selected “orbits of interest” in the cis-lunar and the Sun–Earth systems. The robustness and efficacy of the approach instill confidence in its applicability for realistic mission design scenarios. Full article
(This article belongs to the Special Issue Spacecraft Orbit Transfers)
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16 pages, 4142 KiB  
Article
Seasonal Variations in Lunar-Assisted GEO Transfer Capability for Southward Launch
by Su-Jin Choi and Hoonhee Lee
Aerospace 2024, 11(4), 321; https://doi.org/10.3390/aerospace11040321 - 19 Apr 2024
Viewed by 1094
Abstract
The launch azimuth of the Naro Space Center is limited toward the south of the Korean peninsula, at 170 ± 10 degrees, suitable for the polar orbit, sun-synchronous orbit, and safety range issues. In this circumstance, one option to send a satellite into [...] Read more.
The launch azimuth of the Naro Space Center is limited toward the south of the Korean peninsula, at 170 ± 10 degrees, suitable for the polar orbit, sun-synchronous orbit, and safety range issues. In this circumstance, one option to send a satellite into GEO is to perform a dog-leg maneuver during ascent, thus forming a medium-inclination orbit under such a restrictive condition. However, this option requires an immense amount of energy for the dog-leg maneuver, as well as a plane change maneuver. The only remaining option is to raise the apogee to the Moon, utilizing lunar gravity to lower the inclination to near zero and then returning to the vicinity of the Earth at an altitude of 35,786 km without maneuver. In order to design lunar-assisted GEO transfer, all feasible paths are defined, but questions remain about how seasonal variations affect all these potential paths. Therefore, this study aims to design and analyze all available trajectories for the year 2031 using a high-fidelity dynamic model, root-finding algorithm, and well-arranged initial conditions, focusing on the impact of seasonal trends. The simulation results indicate that cislunar free-return trajectories generally require less ΔV compared to circumlunar free-return trajectories, and circumlunar trajectories are minimally affected by lunisolar effects due to their relatively short return time of flight. Conversely, cislunar trajectories show seasonal variations, so spring and fall seasons require up to 20 m/s less ΔV than summer and winter seasons due to the relatively long time of return duration. Full article
(This article belongs to the Special Issue Spacecraft Orbit Transfers)
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23 pages, 6020 KiB  
Article
A Pattern Search Method to Optimize Mars Exploration Trajectories
by Su-Jin Choi, Hongjae Kang, Keejoo Lee and Sejin Kwon
Aerospace 2023, 10(10), 827; https://doi.org/10.3390/aerospace10100827 - 22 Sep 2023
Cited by 3 | Viewed by 1120
Abstract
The Korean National Space Council recently released “Mars Exploration 2045” as part of its future strategic plan. The operations for a Mars explorer can be defined based on domestically available capabilities, such as ground operations, launch, in-space transport and deep space link. Accordingly, [...] Read more.
The Korean National Space Council recently released “Mars Exploration 2045” as part of its future strategic plan. The operations for a Mars explorer can be defined based on domestically available capabilities, such as ground operations, launch, in-space transport and deep space link. Accordingly, all of our exploration scenarios start from the Naro space center, and the pathway to Mars is optimized using an objective function that minimizes the required ∆V. In addition, the entire phase of Mars orbit insertion should remain in contact with our deep space antennas, a measure that is imposed as an operational constraint. In this study, a pattern search method is adopted, as it can handle a nonlinear problem without relying on the derivatives of the objective function, and optimal trajectories are generated on a daily basis for a 15-day launch period. The robustness of this direct search method is confirmed by consistently converged solutions showing, in particular, that the ascending departure requires slightly less ∆V than the descending departure on the order of 10 m/s. Subsequently, mass estimates are made for a Mars orbiter and a kick stage to determine if the desired ∆V is achievable with our eco-friendly in-space propulsion system when launched from our indigenous launch vehicle, KSLV-II. Full article
(This article belongs to the Special Issue Spacecraft Orbit Transfers)
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