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11 pages, 540 KiB  
Article
Research on Waveform Adaptability Based on Lunar Channels
by Min Jia, Jonghui Li, Zijie Wang, Chao Zhao, Daifu Yan, Hui Wang, Dongmei Li and Weiran Sun
Electronics 2024, 13(24), 5047; https://doi.org/10.3390/electronics13245047 - 22 Dec 2024
Viewed by 482
Abstract
In recent years, the focus of space research and exploration by various countries and international space agencies has been on the return of humans to the moon. Astronauts on lunar missions need to utilize network communication and exchange data. Against this backdrop, it [...] Read more.
In recent years, the focus of space research and exploration by various countries and international space agencies has been on the return of humans to the moon. Astronauts on lunar missions need to utilize network communication and exchange data. Against this backdrop, it is necessary to consider the performance of communication systems and the extreme conditions of the lunar environment, such as signal attenuation and frequency selection, to ensure the reliability and stability of communication systems. Therefore, providing technical performance adapted to the lunar environment is crucial. In this article, we investigated the applicability of Orthogonal Frequency Division Multiple Access (OFDMA) and Single-Carrier Frequency Division Multiple Access (SC-FDMA) waveforms in the lunar communication environment. Specifically, we used Peak-to-Average Power Ratio (PAPR) and Bit Error Rate (BER) as performance indicators. By studying the impact of different modulation schemes and cyclic prefix lengths on communication performance, we completed the research on waveform adaptability based on lunar channels. Simulation results indicate that the transmission structure we designed can meet the system-level performance requirements of lunar communications. This research provides valuable insights for the design and optimization of communication systems for future lunar missions, paving the way for the seamless integration of advanced ground technologies in extraterrestrial environments. Full article
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Figure 1
<p>Propagation path of lunar electromagnetic waves.</p>
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<p>BER performance versus the length of CP. (<b>a</b>) Uplink BER performance versus the length of CP in 20 MHz bandwidth. (<b>b</b>) Downlink BER performance versus the length of CP in 20 MHz bandwidth. (<b>c</b>) Uplink BER performance versus the length of CP in 10 MHz bandwidth. (<b>d</b>) Downlink BER performance versus the length of CP in 10 MHz bandwidth.</p>
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<p>Performance comparison of different modulation methods. (<b>a</b>) Performance comparison of different modulation methods for 20 M bandwidth. (<b>b</b>) Performance comparison of different modulation methods for 10 M bandwidth.</p>
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<p>Comparison of PAPR for different modulation schemes and orders. (<b>a</b>) Comparison of PAPR for different modulation schemes under 20 MHz bandwidth. (<b>b</b>) Comparison of PAPR for different modulation orders of QAM under 20 MHz bandwidth. (<b>c</b>) Comparison of PAPR for different modulation orders of APSK under 20 MHz bandwidth. (<b>d</b>) Comparison of PAPR for different modulation orders of PSK under 20 MHz bandwidth.</p>
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<p>Comparison of PAPR for different modulation schemes and orders. (<b>a</b>) Comparison of PAPR for different modulation schemes under 10MHz bandwidth. (<b>b</b>) Comparison of PAPR for different modulation orders of QAM under 10MHz bandwidth. (<b>c</b>) Comparison of PAPR for different modulation orders of APSK under 10MHz bandwidth. (<b>d</b>) Comparison of PAPR for different modulation orders of PSK under 10MHz bandwidth.</p>
Full article ">Figure 5 Cont.
<p>Comparison of PAPR for different modulation schemes and orders. (<b>a</b>) Comparison of PAPR for different modulation schemes under 10MHz bandwidth. (<b>b</b>) Comparison of PAPR for different modulation orders of QAM under 10MHz bandwidth. (<b>c</b>) Comparison of PAPR for different modulation orders of APSK under 10MHz bandwidth. (<b>d</b>) Comparison of PAPR for different modulation orders of PSK under 10MHz bandwidth.</p>
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<p>Comparison of BER performance for different modulation schemes. (<b>a</b>) Comparison of QAM and PSK modulation BER performance in 20 MHz bandwidth. (<b>b</b>) Comparison of BER performance for different modulation schemes in 20 MHz bandwidth. (<b>c</b>) Comparison of QAM and PSK modulation BER performance in 10 MHz bandwidth. (<b>d</b>) Comparison of QAM and PSK modulation BER performance in 10 MHz bandwidth.</p>
Full article ">Figure 6 Cont.
<p>Comparison of BER performance for different modulation schemes. (<b>a</b>) Comparison of QAM and PSK modulation BER performance in 20 MHz bandwidth. (<b>b</b>) Comparison of BER performance for different modulation schemes in 20 MHz bandwidth. (<b>c</b>) Comparison of QAM and PSK modulation BER performance in 10 MHz bandwidth. (<b>d</b>) Comparison of QAM and PSK modulation BER performance in 10 MHz bandwidth.</p>
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22 pages, 475 KiB  
Article
On Astronomical Materials in Buddhist Scriptures
by Weixing Niu
Religions 2024, 15(11), 1321; https://doi.org/10.3390/rel15111321 - 29 Oct 2024
Viewed by 993
Abstract
There are many foreign astronomical materials that were preserved in the Chinese translation of Buddhist canons. From the content, these astronomical materials include cosmology theories, lunar mansion systems, calendrical data, etc. These astronomical materials are important evidence for the exchange and dissemination of [...] Read more.
There are many foreign astronomical materials that were preserved in the Chinese translation of Buddhist canons. From the content, these astronomical materials include cosmology theories, lunar mansion systems, calendrical data, etc. These astronomical materials are important evidence for the exchange and dissemination of astronomy between ancient civilizations. This paper aims to sort out and analyze the astronomical materials preserved in the Chinese translation of Buddhist canons, classifying and differentiating the content of astronomy, which was foreign to China, tracing the origins of these astronomical knowledge, discussing their impact on local astronomy in China, and evaluating the preservation form, characteristics, reliability, functionality, and limitations of these astronomical materials. Through the above discussion, this paper will demonstrate the core meaning of the historical view of transcultural transmission of sciences and technology, which is ‘knowledge progresses through dissemination and civilization thrives through communication’. Full article
21 pages, 6898 KiB  
Article
Investigating the Impact of Lunar Rover Structure and Lunar Surface Characteristics on Antenna Performance
by Rida Gadhafi, Elham Serria, Sara AlMaeeni, Husameldin Mukhtar, Raed Abd-Alhameed and Wathiq Mansoor
Sensors 2024, 24(16), 5361; https://doi.org/10.3390/s24165361 - 19 Aug 2024
Viewed by 1330
Abstract
This article explores the influence of lunar regolith and rover structure, such as mast design and material composition, on antenna parameters. It focuses on the distinctive difficulties of communication in the lunar environment, which need specialized antenna solutions. This study specifically examines the [...] Read more.
This article explores the influence of lunar regolith and rover structure, such as mast design and material composition, on antenna parameters. It focuses on the distinctive difficulties of communication in the lunar environment, which need specialized antenna solutions. This study specifically examines the performance of antennas on the lunar Rashid rover within the Atlas crater, a landing site on the moon, considering two antenna types: a sleeve dipole antenna and an all-metal patch antenna. Thermal analyses reveal temperatures in the Atlas crater can exceed 80 °C during lunar mid-day. The findings highlight the effect of different materials used as thermal coatings for Rashid rover antennas, as well as the influence of rover materials on antenna performance. Furthermore, this study extends to analyze the conductivity and depth of lunar regolith within the Atlas crater. Given the critical role of antennas in wireless communication, understanding how lunar regolith properties affect antenna performance is essential. This research contributes to the creation of a strong communication system for the Rashid rover and future lunar missions by considering the features of the lunar regolith in addition to the rover’s size and material attributes. Full article
(This article belongs to the Section Communications)
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<p>(<b>a</b>) Rashid rover back view, (<b>b</b>) Rashid rover three-dimensional view.</p>
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<p>Designed sleeve dipole antenna, (<b>a</b>) sleeve dipole antenna, (<b>b</b>) sleeve dipole antenna with tube.</p>
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<p>Designed patch antenna.</p>
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<p>Simulated model of Rashid rover with sleeve dipole antenna and patch antenna.</p>
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<p>Simulated characteristics of the sleeve dipole antenna. (<b>a</b>) Reflection coefficient for the 55.7 mm antenna and the 159.5 mm antenna with a tube, (<b>b</b>) corresponding radiation pattern at the YZ-plane. The coordinates represent the orientation of the antenna.</p>
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<p>(<b>a</b>) Reflection coefficient (S<sub>11</sub>) for the sleeve dipole antenna with acrylic paint and polyimide film coating. (<b>b</b>) Radiation pattern (YZ-plane) for the sleeve dipole antenna with different material coatings. The coordinates represent the orientation of the antenna.</p>
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<p>Reflection coefficient (S<sub>11</sub>) of the patch antenna.</p>
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<p>Radiation pattern of the patch antenna. (<b>a</b>) XZ-plane, (<b>b</b>) YZ-plane. The coordinates represent the orientation of the antenna.</p>
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<p>Reflection coefficient of the sleeve dipole antenna for the conductivities 1 × 10<sup>−9</sup> and 1 × 10<sup>−14</sup>.</p>
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<p>Radiation pattern of the sleeve dipole antenna for the conductivities 1 × 10<sup>−9</sup> (red color) and 1 × 10<sup>−14</sup> (green color). (<b>a</b>) YZ-plane, (<b>b</b>) XZ-plane. The coordinates represent the orientation of the antenna.</p>
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<p>Reflection coefficient of the patch antenna at different heights from lunar regolith.</p>
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<p>Radiation pattern of the patch antenna at two different heights, 718 mm (red curves) and 98 mm (orange curves), from lunar regolith at the XZ- as well as YZ-planes. (<b>a</b>) Pattern at the XZ-plane when the antenna is at a height of 718 mm. (<b>b</b>) Pattern at the XZ-plane when the antenna is at a height of 98 mm. (<b>c</b>) Pattern at the YZ-plane when the antenna is at height of 718 mm and (<b>d</b>) pattern at the YZ-plane when the antenna is at a height of 98 mm. The coordinates represent the orientation of the antenna.</p>
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<p>Reflection coefficient (<b>a</b>) and radiation pattern (<b>b</b>) of the sleeve dipole antenna while integrated with the rover structure. The red color shows the pattern at the XZ-plane and the green color shows the pattern at the YZ-plane. The coordinates represent the orientation of the antenna.</p>
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<p>Reflection coefficient (<b>a</b>) and radiation pattern (<b>b</b>) of the patch antenna while integrated with the rover structure; the red color shows the pattern at the XZ-plane and the green color shows the pattern at the YZ-plane. The coordinates represent the orientation of the antenna.</p>
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<p>Lunar day in Atlas crater, 24 April to 9 May 2023. ALT is the elevation and AZ is the azimuth at the prime landing site.</p>
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<p>Reflection coefficient and radiation pattern of the patch antenna for a 90° clockwise (blue color), 90° counterclockwise (green color), and 180° antenna patch facing the regolith (red color). (<b>a</b>) reflection coefficient (<b>b</b>) pattern at the XZ-plane, (<b>c</b>) pattern at the YZ-plane.</p>
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<p>Reflection coefficient and radiation pattern of the sleeve dipole antenna integrated with the rover placed on top of Atlas crater for conductivities of 1 × 10<sup>−9</sup> (red color) and 1 × 10<sup>−14</sup> (green color). (<b>a</b>) reflection coefficient (<b>b</b>) XZ-plane (<b>c</b>) YZ-plane. The coordinates represent the orientation of the antenna.</p>
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<p>Reflection coefficient and radiation pattern of the patch antenna integrated with the rover placed on top of Atlas crater for conductivities of 1 × 10<sup>−9</sup> (red color) and 1 × 10<sup>−14</sup> (green color). (<b>a</b>) reflection coefficient, (<b>b</b>) XZ-plane (<b>c</b>) YZ-plane. The coordinates represent the orientation of the antenna.</p>
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23 pages, 10006 KiB  
Article
Operational Tests for Delay-Tolerant Network between the Moon and Earth Using the Korea Pathfinder Lunar Orbiter in Lunar Orbit
by Inkyu Kim, Sang Ik Han and Dongsoo Har
Electronics 2024, 13(15), 3088; https://doi.org/10.3390/electronics13153088 - 4 Aug 2024
Viewed by 1210
Abstract
The Korea Pathfinder Lunar Orbiter (KPLO) was launched on 5 August 2022, equipped on the SpaceX Falcon 9 launch vehicle. At present, the KPLO is effectively carrying out its scientific mission in lunar orbit. The KPLO serves as a cornerstone for the development [...] Read more.
The Korea Pathfinder Lunar Orbiter (KPLO) was launched on 5 August 2022, equipped on the SpaceX Falcon 9 launch vehicle. At present, the KPLO is effectively carrying out its scientific mission in lunar orbit. The KPLO serves as a cornerstone for the development and validation of Korean space science and deep space technology. Among its payloads is the DTNPL, enabling the first-ever test of delay-tolerant network (DTN) technology for satellites in lunar orbit. DTN technology represents a significant advancement in space communication, offering stable communication capabilities characterized by high delay tolerance, reliability, and asymmetric communication speeds—a necessity for existing satellite and space communication systems to evolve. In this paper, we briefly give an overview of the Korea Lunar Exploration Program (KLEP) and present scientific data gathered through the KPLO mission. Specifically, we focus on the operational tests for DTN-ION conducted for message and file transfer, as well as real-time video streaming, during the initial operations of the KPLO. Lastly, this study offers insights and lessons learned from KPLO DTNPL operations, with the goal of providing valuable guidance for future advancements in space communication. Full article
(This article belongs to the Special Issue Delay Tolerant Networks and Applications, 2nd Edition)
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<p>KPLO hardware configuration. Reproduced with permission from KPLO Danuri Launch Press Kit; published by KARI, 2022 [<a href="#B15-electronics-13-03088" class="html-bibr">15</a>].</p>
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<p>Drygalski crater taken by KPLO LUTI. Reproduced with permission from <a href="https://www.kari.re.kr/kplo/multimedia/" target="_blank">https://www.kari.re.kr/kplo/multimedia/</a> (accessed on 20 February 2024); published by KARI [<a href="#B18-electronics-13-03088" class="html-bibr">18</a>].</p>
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<p>KMAG configuration. Reproduced with permission from KARI, <a href="https://pda.kasi.re.kr/kmag.php?lang=en" target="_blank">https://pda.kasi.re.kr/kmag.php?lang=en</a> (accessed on 23 February 2024); published by KASI [<a href="#B24-electronics-13-03088" class="html-bibr">24</a>].</p>
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<p>Photo of Sverdrup crater taken by ShadowCam. Reproduced with permission from <a href="https://www.kari.re.kr/kplo/multimedia/" target="_blank">https://www.kari.re.kr/kplo/multimedia/</a> (accessed on 20 February 2024); published by KARI [<a href="#B18-electronics-13-03088" class="html-bibr">18</a>].</p>
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<p>DTN architecture—Bundle and other protocol stacks with CLA.</p>
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<p>Operational test configuration for DTNPL.</p>
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<p>The flow diagram for KPLO DTN operational tests.</p>
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<p>Communication protocol architecture for DTNPL operational tests.</p>
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<p>Operational test result: message transfer.</p>
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<p>Operational test result: file transfer.</p>
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<p>Operational test result: real-time video streaming.</p>
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<p>Operational test result: file transfer under link interruption.</p>
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27 pages, 4239 KiB  
Article
Code-Based Differential GNSS Ranging for Lunar Orbiters: Theoretical Review and Application to the NaviMoon Observables
by Anaïs Delépaut, Alex Minetto and Fabio Dovis
Remote Sens. 2024, 16(15), 2755; https://doi.org/10.3390/rs16152755 - 28 Jul 2024
Cited by 1 | Viewed by 1152
Abstract
In the near future, international space agencies have planned to achieve significant milestones in investigating the utilization of Global Navigation Satellite Systems (GNSS) within and beyond the current space service volume up to their application to lunar missions. These initiatives aim to demonstrate [...] Read more.
In the near future, international space agencies have planned to achieve significant milestones in investigating the utilization of Global Navigation Satellite Systems (GNSS) within and beyond the current space service volume up to their application to lunar missions. These initiatives aim to demonstrate the feasibility of GNSS navigation at lunar altitudes. Based on the outcomes of such demonstrations, dozens of lunar missions will likely be equipped with a GNSS receiver to support autonomous navigation in the lunar proximity. Relying on non-invasive, consolidated differential techniques, GNSS will enable baseline estimation, thus supporting a number of potential applications to lunar orbiters such as collaborative navigation, formation flight, orbital manoeuvers, remote sensing, augmentation systems and beyond. Unfortunately, the large dynamics and the geometry of such differential GNSS scenarios set them apart from current terrestrial and low-earth orbit use cases. These characteristics result in an increased sensitivity to measurements time misalignment among orbiters. Hence, this paper offers a review of baseline estimation methods and characterizes the divergences and limitations w.r.t. to terrestrial applications. The study showcases the estimation of the baseline length between a lunar CubeSat mission, VMMO, and the communication relay Lunar Pathfinder mission. Notably, real GNSS measurements generated by an Engineering Model of the NaviMoon receiver in the European Space Agency (ESA/ESTEC) Radio Navigation Laboratory are utilized. A radio-frequency constellation simulator is used to generate the GNSS signals in these hardware-in-the-loop tests. The performed analyses showed the invalidity of common terrestrial differential GNSS ranging techniques for space scenarios due to the introduction of significant biases. Improved ranging algorithms were proposed and their potential to cancel ranging errors common to both receivers involved was confirmed. Full article
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<p>Pictorial view of differential GNSS ranging both for terrestrial applications and space scenarios. The symbol * denotes the user id where it can be either <span class="html-italic">i</span> or <span class="html-italic">j</span>.</p>
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<p>Schematic of the GNSS transmitted signals in deep space. The main lobe beamwidth value was taken from the interoperable GNSS SSV book [<a href="#B8-remotesensing-16-02755" class="html-bibr">8</a>].</p>
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<p>Schematic of the GNSS scenario for VMMO and Pathfinder.</p>
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<p>ISR and relative velocity between VMMO and Pathfinder over a 4 h test window.</p>
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<p>Doppler shifts between Pathfinder and the GNSS satellites over a 4 h test window.</p>
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<p>DOP and Visibility of common GNSS satellites.</p>
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<p><math display="inline"><semantics> <mrow> <mi>C</mi> <mo>/</mo> <msub> <mi>N</mi> <mn>0</mn> </msub> </mrow> </semantics></math> tracks of the VMMO mission.</p>
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<p>Inter steering vectors angles.</p>
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<p>Test bench block diagram.</p>
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<p>ISR estimation over time.</p>
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<p>ISV estimation over time.</p>
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<p>ISV estimation over time.</p>
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<p>Orbital error residuals on SD measurements.</p>
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<p>ISR RMSE over time with worst-case SISE.</p>
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<p>ISR estimation from simulations vs from NaviMoon.</p>
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31 pages, 12799 KiB  
Article
Day/Night Power Generator Station: A New Power Generation Approach for Lunar and Martian Space Exploration
by Thomas F. Arciuolo, Miad Faezipour and Xingguo Xiong
Electronics 2024, 13(14), 2859; https://doi.org/10.3390/electronics13142859 - 19 Jul 2024
Viewed by 1081
Abstract
In the not-too-distant future, humans will return to the Moon and step foot for the first time on Mars. Eventually, humanity will colonize these celestial bodies, where living and working will be commonplace. Energy is fundamental to all life. The energy that people [...] Read more.
In the not-too-distant future, humans will return to the Moon and step foot for the first time on Mars. Eventually, humanity will colonize these celestial bodies, where living and working will be commonplace. Energy is fundamental to all life. The energy that people use to sustain themselves on Earth, and in particular on these other worlds, is the integrated, safe production of electrical power, day and night. This paper proposes a radically new solution to this problem: Solar Tracking by day and a Solar Rechargeable Calcium Oxide Chemical Thermoelectric Reactor by night. Called the “Robotic End Effector for Lunar and Martian Geological Exploration of Space” (REEGES) Day/Night Power Generator Station, this form of thermoelectric power generation is mathematically modeled, simulation is performed, and a concept model design is demonstrated in this paper. The results of the presented simulation show the maximum total system output capability is 9.89 V, 6.66 A, and 65.9 W, with an operating time of up to 12 h, through a scalable design. This research provides instructions to the Space Research Community on a complete and novel development methodology for creating fully customized, configurable, safe, and reliable solar/thermoelectric day/night power generators, specifically meant for use on the Moon and Mars, using the Proportional-Integral-Derivative++ (PID++) Humanoid Motion Control Algorithm for its operation on a computationally lightweight microcontroller. Full article
(This article belongs to the Special Issue Feature Papers in Circuit and Signal Processing)
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<p>Flow diagram of the overall design steps for the proposed power generator station.</p>
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<p>Single thermoelectric couple where <span class="html-italic">T<sub>h</sub></span> &gt; <span class="html-italic">T<sub>c</sub></span>.</p>
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<p>Area-to-length ratio of TE power generator device.</p>
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<p>(<b>a</b>) Top view and (<b>b</b>) Side view of Thermocouple.</p>
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<p>Voltage regulation on ToC.</p>
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<p>Thermal Radiator for ToC.</p>
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<p>Power Station—Thermoelectric Generator—Series Portion (Only)—1 GΩ and 2.5 Ω Loads.</p>
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<p>P-Type Legs.</p>
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<p>N-Type Legs.</p>
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<p>Tungsten Pads.</p>
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<p>Copper connectors.</p>
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<p>Geometry model.</p>
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<p>Geometry model mesh.</p>
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<p>Surface Temperature (°K).</p>
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<p>Isosurface Temperature (°K).</p>
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<p>Multislice electric potential (V) (1 GΩ Load).</p>
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<p>Terminal voltage (V) (1 GΩ Load).</p>
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<p>Terminal current (A) (1 GΩ Load).</p>
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<p>Multislice electric potential (V) (2.5 Ω Load).</p>
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<p>Terminal voltage (V) (2.5 Ω Load).</p>
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<p>Terminal current (A) (2.5 Ω Load).</p>
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<p>Power station illustration.</p>
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<p><span class="html-italic">Kp</span>, <span class="html-italic">Ki,</span> and <span class="html-italic">Kd</span> parameters for PID++ Sponge Compression—Vmax = 20 cnts/ms, Adesired = 0.015 cnts/ms<sup>2</sup>.</p>
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<p>Encoder position, output and speed plots for PID++ Sponge Compression—Vmax = 20 cnts/ms, Adesired = 0.015 cnts/ms<sup>2</sup>.</p>
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29 pages, 7672 KiB  
Article
Electric Sail Test Cube–Lunar Nanospacecraft, ESTCube-LuNa: Solar Wind Propulsion Demonstration Mission Concept
by Andris Slavinskis, Mario F. Palos, Janis Dalbins, Pekka Janhunen, Martin Tajmar, Nickolay Ivchenko, Agnes Rohtsalu, Aldo Micciani, Nicola Orsini, Karl Mattias Moor, Sergei Kuzmin, Marcis Bleiders, Marcis Donerblics, Ikechukwu Ofodile, Johan Kütt, Tõnis Eenmäe, Viljo Allik, Jaan Viru, Pätris Halapuu, Katriin Kristmann, Janis Sate, Endija Briede, Marius Anger, Katarina Aas, Gustavs Plonis, Hans Teras, Kristo Allaje, Andris Vaivads, Lorenzo Niccolai, Marco Bassetto, Giovanni Mengali, Petri Toivanen, Iaroslav Iakubivskyi, Mihkel Pajusalu and Antti Tammadd Show full author list remove Hide full author list
Aerospace 2024, 11(3), 230; https://doi.org/10.3390/aerospace11030230 - 14 Mar 2024
Cited by 2 | Viewed by 2739
Abstract
The electric solar wind sail, or E-sail, is a propellantless interplanetary propulsion system concept. By deflecting solar wind particles off their original course, it can generate a propulsive effect with nothing more than an electric charge. The high-voltage charge is applied to one [...] Read more.
The electric solar wind sail, or E-sail, is a propellantless interplanetary propulsion system concept. By deflecting solar wind particles off their original course, it can generate a propulsive effect with nothing more than an electric charge. The high-voltage charge is applied to one or multiple centrifugally deployed hair-thin tethers, around which an electrostatic sheath is created. Electron emitters are required to compensate for the electron current gathered by the tether. The electric sail can also be utilised in low Earth orbit, or LEO, when passing through the ionosphere, where it serves as a plasma brake for deorbiting—several missions have been dedicated to LEO demonstration. In this article, we propose the ESTCube-LuNa mission concept and the preliminary cubesat design to be launched into the Moon’s orbit, where the solar wind is uninterrupted, except for the lunar wake and when the Moon is in the Earth’s magnetosphere. This article introduces E-sail demonstration experiments and the preliminary payload design, along with E-sail thrust validation and environment characterisation methods, a cis-lunar cubesat platform solution and an early concept of operations. The proposed lunar nanospacecraft concept is designed without a deep space network, typically used for lunar and deep space operations. Instead, radio telescopes are being repurposed for communications and radio frequency ranging, and celestial optical navigation is developed for on-board orbit determination. Full article
(This article belongs to the Special Issue Advances in CubeSat Sails and Tethers)
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<p>Electric Sail Test Cube–Lunar Nanospacecraft (ESTCube-LuNa) experiment design in the Moon’s orbit (adapted from [<a href="#B42-aerospace-11-00230" class="html-bibr">42</a>]). The solar wind, arriving from the right, is a space plasma flow of protons and electrons. The solar wind protons are deflected by the positively charged electrostatic sheath around the E-sail, creating thrust (spacecraft propulsion) as a result. The electron emitter compensates for the electron current gathered by the tethers by continuously pumping out negative charge from the spacecraft. Artwork credit: Mario F. Palos, Anna Maskava and Rute Marta Jansone.</p>
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<p>ESTCube-LuNa spin rate modification experiment. The solar wind, arriving from the right, meets the nanospacecraft, which is rotating anti-clockwise, and exerts the E-sail force, which is turned into a torque. The torque is changing the ESTCube-LuNa’s angular velocity. The spin rate modification experiment can be performed twice a year when the inertially fixed spin plane is aligned with the solar wind flow. Artwork credit: Mario F. Palos, Anna Maskava and Rute Marta Jansone.</p>
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<p>ESTCube-LuNa thrust experiment results from GMAT. LEFT: Orbital view in which the red line indicates the orbital sector of ESTCube-LuNa moving towards the Sun—the thrust period for reducing altitude. The yellow line is from the centre of the Moon to the Sun. RIGHT: Comparison of the orbital period between a “NoSailClone” spacecraft without thrust and ESTCube-LuNa, which emulates the E-sail thrust magnitude and direction with GMAT’s electric thrusters. For the first 0.16 days, both spacecrafts are in the same orbit, and then ESTCube-LuNa starts thrusting. As a result of the applied thrust, the orbital period is reduced along with the altitude. The thrust is not applied while in the eclipse.</p>
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<p>The ESTCube-2 Coulomb drag propulsion payload design for low Earth orbit (<b>top</b>) and the E-sail tether with a grey hair for comparison (<b>bottom</b>). The ESTCube-2 payload design includes both the negative plasma brake mode for deorbiting and the positive E-sail mode for demonstrating the electron emitters. To maximise the tether length, the ESTCube-LuNa concept allocates a whole cubesat unit for the E-sail reel and motor with E-sail control electronics implemented separately.</p>
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<p>ESTCube-LuNa thruster and tether deployment directions. An 8-thruster system allows us to control the spin rate and the spin plane. Spin rate control is necessary for E-sail tether deployment. Spin plane control is available before tether deployment. When the tether is deployed, the spin plane thrusters can be used to tilt the spacecraft body for communication sessions.</p>
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<p>Simulation results of deploying the first 60 <math display="inline"><semantics> <mi mathvariant="normal">m</mi> </semantics></math> of the ESTCube-LuNa E-sail tether: spacecraft angular velocity, tether tension and length, and the centre-of-mass (CoM) shift of the spacecraft–tether system. Spin-up and deployment are performed in steps by considering the tether tension and deflection angle as safety factors. The increased tension upon the initial deployment must be analysed further in terms of safety and dynamical aspects.</p>
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<p>Simulation results of deploying the full 2 <math display="inline"><semantics> <mi mathvariant="normal">k</mi> </semantics></math><math display="inline"><semantics> <mi mathvariant="normal">m</mi> </semantics></math> ESTCube-LuNa tether. During deployment, the tether tension is maintained between 1 <math display="inline"><semantics> <mi mathvariant="normal">m</mi> </semantics></math><math display="inline"><semantics> <mi mathvariant="normal">N</mi> </semantics></math> and 5 <math display="inline"><semantics> <mi mathvariant="normal">m</mi> </semantics></math><math display="inline"><semantics> <mi mathvariant="normal">N</mi> </semantics></math>, except during the first step, as explained above.</p>
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<p>Simulation results of deploying the first 1 <math display="inline"><semantics> <mi mathvariant="normal">m</mi> </semantics></math> of ESTCube-LuNa tether using an unreeling speed of 1 <math display="inline"><semantics> <mi mathvariant="normal">c</mi> </semantics></math><math display="inline"><semantics> <mi mathvariant="normal">m</mi> </semantics></math>. The initial angular velocity was chosen to provide approximately 1 <math display="inline"><semantics> <mi mathvariant="normal">m</mi> </semantics></math><math display="inline"><semantics> <mi mathvariant="normal">N</mi> </semantics></math> of tether tension.</p>
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<p>Sketch of the inertial reference frame, the E-sail spin axis, and control angles <math display="inline"><semantics> <mrow> <mi>ζ</mi> <mo>,</mo> <mi>ψ</mi> </mrow> </semantics></math>.</p>
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<p>An exploded view of ESTCube-LuNa showing the preliminary volume allocation of payloads and subsystems inside the nanospacecraft. The side with thruster, LPs and navigation camera control boxes requires careful system engineering to place thrusters, control electronics, harness and wiring to LPs and TCN cameras.</p>
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<p>An early ESTCube-LuNa concept of operations: initial ideas and concepts for communications and navigation. Artwork credit: Anna Maskava, Mario F. Palos, Karl-Mattias Moor and Rute Marta Jansone.</p>
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<p>Proposed antenna solutions for ESTCube-LuNa. EnduroSat X-band patch antenna for data downlink and ranging (<b>left</b>) and ISISPACE turnstile antenna for UHF telemetry and command (<b>right</b>).</p>
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<p>HSCOM RT-16 (<b>left</b>) and RT-32 (<b>right</b>) dishes in Irbene, Latvia.</p>
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<p>The ESTCube-LuNa real-time 3D (RT3D) navigation concept in Unreal Engine 5 with textures from the Solar System Scope [<a href="#B61-aerospace-11-00230" class="html-bibr">61</a>]. The image on the left shows the Moon; on the right, the Sun and the Earth, as imaged by two out of five 120<math display="inline"><semantics> <mo>°</mo> </semantics></math> FoV cameras. By imaging three celestial objects, triangulation can be used to determine the ESTCube-LuNa position in lunar orbit, as described in <a href="#sec5dot5dot2-aerospace-11-00230" class="html-sec">Section 5.5.2</a>.</p>
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17 pages, 6830 KiB  
Article
Filtering Strategies for Relative Navigation in Lunar Scenarios Using LCNS
by Marco Sabatini and Giovanni B. Palmerini
Aerospace 2024, 11(1), 59; https://doi.org/10.3390/aerospace11010059 - 8 Jan 2024
Cited by 1 | Viewed by 1486
Abstract
This paper investigates the performance of the forthcoming lunar navigation satellite systems for estimating not only the position of an onboard receiver in a lunar inertial reference frame but also, and with a consistent accuracy, the relative position between two or more spacecraft [...] Read more.
This paper investigates the performance of the forthcoming lunar navigation satellite systems for estimating not only the position of an onboard receiver in a lunar inertial reference frame but also, and with a consistent accuracy, the relative position between two or more spacecraft in proximity. This could be the case of two spacecraft performing a rendezvous, of a lander released by an orbiter, or the case of the permanent relative navigation service for a formation of satellites around the Moon. The considered observables are the pseudorange and pseudorange-rate measurements provided by the upcoming lunar communication and navigation system (LCNS), expected to support lunar missions. A single-stage Kalman filter is implemented, and its performance is demonstrated through error statistics, which are then compared to what can be achieved with sequential filtering. Full article
(This article belongs to the Special Issue GNC for the Moon, Mars, and Beyond)
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<p>3D representation of the ELFO constellation in the Moon Inertial reference frame. Notice the apolunes located above the southern hemisphere to best service in the southern polar cap. Blue, red, black and dotted green represents the orbits of the four ELFO satellites.</p>
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<p>Geometric visibility conditions. Red lines indicate a visibility condition, blue-dotted lines indicate a condition of non-visibility.</p>
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<p>Visibility conditions as a function of the orbit inclination.</p>
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<p>Number of visible satellites as a function of the latitude for a polar orbiter.</p>
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<p>Visibility conditions for a polar orbit, at different RAAN angles.</p>
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<p>Relative motion in the LVLH frame.</p>
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<p>Cascade filter architecture implemented for relative state estimation.</p>
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<p>The architecture of the single-stage UKF for formation navigation.</p>
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<p>Convergence of the single-stage UKF in the case of a cold start: Chief inertial state error norm. Blue line indicates the position RMSE, red line is the number of visible satellites.</p>
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<p>Convergence time comparison of the inertial state using the cascade EKF and the single-stage UKF.</p>
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<p>Convergence of the single-stage UKF and the cascade EKF in the case of a cold start: relative orbital elements error norm.</p>
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<p>Estimate the error norm of the Chief inertial position using the cascade EKF and the single-stage UKF.</p>
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<p>Time behavior of the true and estimated relative orbital elements.</p>
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<p>Percentage difference between the norm of the true and of the estimated relative orbital elements vector.</p>
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<p>Error norm of the estimated relative position with the single-stage UKF and the cascade EKF.</p>
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27 pages, 3736 KiB  
Review
A Review of Lunar Communications and Antennas: Assessing Performance in the Context of Propagation and Radiation
by Elham Serria, Rida Gadhafi, Sara AlMaeeni, Husameldin Mukhtar, Abigail Copiaco, Raed Abd-Alhameed, Frederic Lemieux and Wathiq Mansoor
Sensors 2023, 23(24), 9832; https://doi.org/10.3390/s23249832 - 14 Dec 2023
Cited by 6 | Viewed by 3970
Abstract
Over the previous two decades, a notable array of space exploration missions have been initiated with the primary aim of facilitating the return of both humans and robots from Earth to the moon. The significance of these endeavors cannot be emphasized enough as [...] Read more.
Over the previous two decades, a notable array of space exploration missions have been initiated with the primary aim of facilitating the return of both humans and robots from Earth to the moon. The significance of these endeavors cannot be emphasized enough as numerous entities, both public and private, from across the globe have invested substantial resources into this pursuit. Researchers have committed their efforts to addressing the challenges linked to lunar communication. Even with all of these efforts, only a few of the many suggested designs for communication and antennas on the moon have been evaluated and compared. These designs have also not been shared with the scientific community. To bridge this gap in the existing body of knowledge, this paper conducts a thorough review of lunar surface communication and the diverse antenna designs employed in lunar communication systems. This paper provides a summary of the findings presented in lunar surface communication research while also outlining the assorted challenges that impact lunar communication. Apart from various antenna designs reported in this field, based on their intended usage, two additional classifications are introduced: (a) mission-based antennas—utilized in actual lunar missions—and (b) research-based antennas—employed solely for research purposes. Given the critical need to comprehend and predict lunar conditions and antenna behaviors within those conditions, this review holds immense significance. Its relevance is particularly pronounced in light of the numerous upcoming lunar missions that have been announced. Full article
(This article belongs to the Special Issue Microwave Sensors and Antenna Topology)
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<p>Lunar communication challenges.</p>
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<p>Schematic of the lunar environment [<a href="#B41-sensors-23-09832" class="html-bibr">41</a>].</p>
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<p>Classification of lunar antenna types based on the existing literature.</p>
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<p>(<b>a</b>) CMMA 3-directional view. (<b>b</b>) CMMA prototype [<a href="#B44-sensors-23-09832" class="html-bibr">44</a>].</p>
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<p>(<b>a</b>) fHCFA with dimensions layout. (<b>b</b>) Fabricated fHCFA [<a href="#B44-sensors-23-09832" class="html-bibr">44</a>].</p>
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<p>Quarter elliptical slotted antenna (QESA) [<a href="#B50-sensors-23-09832" class="html-bibr">50</a>].</p>
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<p>Mimo array layout [<a href="#B50-sensors-23-09832" class="html-bibr">50</a>].</p>
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<p>All-metal circular patch antenna [<a href="#B18-sensors-23-09832" class="html-bibr">18</a>].</p>
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<p>Inf-IRA concept and overall diagram [<a href="#B57-sensors-23-09832" class="html-bibr">57</a>].</p>
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<p>Side view of two antennas: conventional impulse-radiating antenna and asymptotic conical dipole fed impulse-radiating antenna [<a href="#B57-sensors-23-09832" class="html-bibr">57</a>].</p>
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<p>(<b>a</b>) Inflated and (<b>b</b>) deflated shape of fabricated inflatable impulse-radiating antennas [<a href="#B57-sensors-23-09832" class="html-bibr">57</a>].</p>
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<p>(<b>a</b>) All-metal single-element short backfire. (<b>b</b>) Waveguide inserted into the main reflector [<a href="#B60-sensors-23-09832" class="html-bibr">60</a>].</p>
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<p>Small-sized active dipole antenna: (<b>a</b>) prototype, (<b>b</b>) antenna frontal projection. Adopted from “The first detection of the solar U+ III association with an antenna prototype for the future lunar observatory” by L. Stanislavsky et al. Research in Astronomy and Astrophysics, (2021) [<a href="#B71-sensors-23-09832" class="html-bibr">71</a>]. Reproduced by permission of RAA. All rights reserved.</p>
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<p>(<b>a</b>) The location of the LPR antennas on the lunar rover. (<b>b</b>) The folding of the CH1 antennas on the lunar rover. Adopted from Lunar Penetrating Radar onboard the Chang’e-3 mission by G.Y. Fang et al., Research in astronomy and astrophysics (2014) [<a href="#B75-sensors-23-09832" class="html-bibr">75</a>]. Reproduced by permission of RAA. All rights reserved.</p>
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<p>The structure of the CH2 antenna. Adopted from Lunar Penetrating Radar onboard the Chang’e-3 mission by G.Y. Fang et al., Research in astronomy and astrophysics (2014) [<a href="#B75-sensors-23-09832" class="html-bibr">75</a>]. Reproduced by permission of RAA. All rights reserved.</p>
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<p>(<b>a</b>) Rashid rover with sleeve dipole antenna. (<b>b</b>) Proposed sleeve dipole structure. Proc. 2023 IEEE CAMA, Genoa, Italy, 2023 [<a href="#B17-sensors-23-09832" class="html-bibr">17</a>].</p>
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19 pages, 1893 KiB  
Article
UWB and MB-OFDM for Lunar Rover Navigation and Communication
by J. de Curtò, I. de Zarzà and Carlos T. Calafate
Mathematics 2023, 11(18), 3835; https://doi.org/10.3390/math11183835 - 7 Sep 2023
Cited by 6 | Viewed by 3212
Abstract
This paper presents a comprehensive study of ultra-wideband (UWB) and multi-band orthogonal frequency-division multiplexing (MB-OFDM) technologies for lunar rover navigation and communication in challenging terrains. Lunar missions pose unique challenges, such as signal propagation in the lunar environment, terrain elevation, and rover movement [...] Read more.
This paper presents a comprehensive study of ultra-wideband (UWB) and multi-band orthogonal frequency-division multiplexing (MB-OFDM) technologies for lunar rover navigation and communication in challenging terrains. Lunar missions pose unique challenges, such as signal propagation in the lunar environment, terrain elevation, and rover movement constraints. To address these challenges, we propose a hybrid communication and navigation system that leverages UWB technology for high-precision positioning and MB-OFDM for robust and high-throughput communication. We develop a realistic simulation framework that incorporates terrain elevation, obstacles, and rover movement constraints, along with a simple fading model for communication. Simulation results demonstrate the effectiveness of the proposed system in navigating lunar rovers to their target locations while maintaining reliable communication links with a lunar lander. A novel approach based on game theory for rover navigation is also presented. The study provides valuable insights into the design and optimization of communication and navigation systems for future lunar missions, paving the way for seamless integration of advanced terrestrial technologies in extraterrestrial environments. Full article
(This article belongs to the Special Issue Modeling and Simulation in Engineering, 3rd Edition)
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<p>Hybrid lunar communication network architecture with satellite relays and surface infrastructure. This diagram shows Earth, the Moon, a lunar base station, and orbiting satellites. The dashed circle represents satellite orbits, while the filled circles on the orbit represent individual satellites. The dotted lines indicate communication links between Earth, the lunar base station, and the satellites. The FSOC link between Earth and the Moon is represented by a thick arrow.</p>
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<p>Diagram and visual illustration of a typical lunar mission. (<b>a</b>) General diagram illustrating the components and architecture of a typical lunar mission. (<b>b</b>) Visual illustration of the setup with a lander communicating with several rovers.</p>
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<p>Path loss vs. distance comparison using UWB and B5G.</p>
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<p>Three-dimensional (3D) representation of a lander acting as anchor and communicating to several rovers.</p>
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<p>Simulation results. (<b>a</b>) Two-dimensional (2D) representation of a simulated scenario with several rovers following a given path. (<b>b</b>) Corresponding elevation of the terrain for the simulated scenario with PERLIN noise.</p>
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<p>Telecommunication analysis. (<b>a</b>) Signal strength (dB) vs. distance (m) between the rover and the lunar lander. (<b>b</b>) Communication delay (s) vs. distance (m) between the rover and the lunar lander.</p>
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<p>Distribution of strategies in the simplified game-theoretic lunar rover navigation simulation.</p>
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28 pages, 8096 KiB  
Article
Integrated Conceptual Design and Parametric Control Assessment for a Hybrid Mobility Lunar Hopper
by Jasmine Rimani, Giordana Bucchioni, Andrea Dan Ryals, Nicole Viola and Stéphanie Lizy-Destrez
Aerospace 2023, 10(8), 669; https://doi.org/10.3390/aerospace10080669 - 27 Jul 2023
Viewed by 1585
Abstract
The lunar lava tubes are envisioned as possible hosting structures for a human base in the Moon’s equatorial regions, providing shelter from radiations, micrometeoroids, and temperature excursion. A first robotic mission is set to scout the habitability of these underground architectures in the [...] Read more.
The lunar lava tubes are envisioned as possible hosting structures for a human base in the Moon’s equatorial regions, providing shelter from radiations, micrometeoroids, and temperature excursion. A first robotic mission is set to scout the habitability of these underground architectures in the near future. The communication inside these underground tunnels is heavily constrained; hence, the scouting system should rely on a high degree of autonomy. At the same time, the exploration system may encounter different types of terrain, requiring an adaptable mobility subsystem able to travel fast on basaltic terrain while avoiding considerable obstacles. This paper presents a cave explorer’s mission study and preliminary sizing targeting the lunar lava tubes. The study proposes using a hybrid mobility system with wheels and thrusters to navigate smoothly inside the lava tubes. The peculiar mobility system of the cave explorer requires an accurate study of the adaptability of its control capabilities with the change of mass for a given set of sensors and actuators. The combination of conceptual design techniques and control assessment gives the engineer a clear indication of the feasible design box for the studied system during the initial formulation phases of a mission. This first part of the study focuses on framing the stakeholders’ needs and identifying the required capabilities of the cave explorer. Furthermore, the study focuses on assessing a design box in terms of mass and power consumption for the cave explorer. Following different mission-level assessments, a more detailed design of the cave explorer is discussed, providing an initial design in terms of mass and power consumption. Finally, the objective shifts toward studying the performances of the guidance, navigation, and control (GNC) algorithms varying the mass of the cave explorer. The GNC significantly impacts the design box of the surface planetary system. Hence, investigating its limitations can indicate the feasibility of mass growth to accommodate, for example, more payload. Full article
(This article belongs to the Special Issue Space Robotics and Mechatronics)
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<p>Overview of the conceptual design methodology.</p>
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<p>Reference frames and main quantities.</p>
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<p>The nominal control scheme.</p>
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<p>Baseline augmentation using MRAC.</p>
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<p>Lava tubes’ mission objectives defined as use cases.</p>
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<p>Growth in total mass, battery mass and power for a system travelling 500 m on one battery discharge at different duty cycles (proportion of the time the system drives against the percentage of time used for payload operations).</p>
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<p>Cave explorer mission objectives modelled as use cases.</p>
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<p>Simple design reference mission (DRM) diagram showing the cave explorer deployment for the envisioned mission architecture (Part 1).</p>
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<p>Simple design reference mission (DRM) diagram showing the skylight explorer deployment for the envisioned mission architecture (Part 2).</p>
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<p>Artistic view of the preliminary concept design of the cave explorer.</p>
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<p>Nominal Controlled Case.</p>
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<p>Altitude variation in presence of mass variation.</p>
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<p>Altitude variation in presence of mass variation- increased thrust.</p>
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<p>Controlled Pitch angle–Inertia variations.</p>
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<p>Lava tubes (Marius Hills, <b>left</b>; Mare Ingenii, <b>center</b>; Mare Tranquillitatis, <b>right</b>). Image from SELENE and LRO missions (figures adapted with permission from Refs. [<a href="#B3-aerospace-10-00669" class="html-bibr">3</a>,<a href="#B71-aerospace-10-00669" class="html-bibr">71</a>,<a href="#B72-aerospace-10-00669" class="html-bibr">72</a>]).</p>
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35 pages, 2366 KiB  
Review
Activities to Promote the Moon as an Absolute Calibration Reference
by Zhenhua Jing, Xiuqing Hu, Yang Wang, Ronghua Wu, Lin Chen, Lu Zhang, Yu Huang, Shuang Wang, Shuang Li and Peng Zhang
Remote Sens. 2023, 15(9), 2431; https://doi.org/10.3390/rs15092431 - 5 May 2023
Cited by 3 | Viewed by 4131
Abstract
The accuracy and consistency of Earth observation (EO) instrument radiometric calibration is a fundamental prerequisite for achieving accurate results and delivering reliable predictions. Frequent calibration and validation (Cal/Val) activities are needed during the instrument’s lifetime, and this procedure is often extended to historical [...] Read more.
The accuracy and consistency of Earth observation (EO) instrument radiometric calibration is a fundamental prerequisite for achieving accurate results and delivering reliable predictions. Frequent calibration and validation (Cal/Val) activities are needed during the instrument’s lifetime, and this procedure is often extended to historical archives. Numerous satellites in orbit and proposed future missions have incorporated lunar observation into their vicarious calibration components over recent years, facilitated by the extreme long-term photometric stability of the Moon. Since the birth of the first lunar calibration reference model, lunar-dependent calibration techniques have developed rapidly, and the application and refinement of the lunar radiometric model have become a welcome research focus in the calibration community. Within the context of the development of lunar observation activities and calibration systems globally, we provide a comprehensive review of the activities and results spawned by treating the Moon as a reference for instrument response and categorize them against the understanding of lunar radiometric reference. In general, this appears to be a process of moving from data to instruments, then back into data, working towards a stated goal. Here we highlight lunar radiometric models developed by different institutions or agencies over the last two decades while reporting on the known limitations of these solutions, with unresolved challenges remaining and multiple lunar observation plans and concepts attempting to address them from various perspectives, presenting a temporal development. We also observe that the methods seeking uncertainty reduction at this stage are rather homogeneous, lacking the combination of approaches or results from lunar surface studies conducted by many spacecraft missions, and joint deep learning methods to extract information. The factors that influence the accuracy of the measurement irradiance may be regulated when practical models arrive. As a central element in lunar calibration, the development of an absolute radiometric datum helps to better understand the Earth system. Full article
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<p>Examples of lunar observations from geostationary and polar-orbiting platforms showing multiple resolutions of the same instrument and illustrating the variety of sampling mechanisms (adapted from [<a href="#B37-remotesensing-15-02431" class="html-bibr">37</a>]).</p>
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<p>Brief summary of lunar irradiance models and lunar observation campaigns along with mission concepts.</p>
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<p>General workflow for formulating lunar reference model.</p>
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<p>Conceptual view of the CPF HySICS instrument observation aboard the International Space Station [<a href="#B169-remotesensing-15-02431" class="html-bibr">169</a>].</p>
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<p>TRUTHS HIS instrument on-orbit observation concept diagram [<a href="#B174-remotesensing-15-02431" class="html-bibr">174</a>].</p>
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<p>LIBRA EMIS lunar observation and transfer calibration schematic.</p>
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9 pages, 2969 KiB  
Technical Note
Ground-to-Drone Optical Pulse Position Modulation Demonstration as a Testbed for Lunar Communications
by Skevos F. E. Karpathakis, Benjamin P. Dix-Matthews, Shane M. Walsh, Ayden S. McCann, David R. Gozzard, Alex M. Frost, Charles T. Gravestock and Sascha W. Schediwy
Drones 2023, 7(2), 99; https://doi.org/10.3390/drones7020099 - 31 Jan 2023
Cited by 2 | Viewed by 4032
Abstract
Free-space optical (FSO) communication promises to bring fibre-like speeds to data transmissions between ground, sky and space. This is becoming more important in light of the increasing volume of data collected by aircraft and spacecraft. The University of Western Australia (UWA) is commissioning [...] Read more.
Free-space optical (FSO) communication promises to bring fibre-like speeds to data transmissions between ground, sky and space. This is becoming more important in light of the increasing volume of data collected by aircraft and spacecraft. The University of Western Australia (UWA) is commissioning optical ground stations to support FSO communications payloads. We propose retroreflected laser links to drones as a useful step towards further ground-to-sky and ground-to-space FSO communications demonstrations. In this paper, we describe the operation of a hardware testbed for a high photon efficiency optical communication physical layer. This testbed was deployed over a slanted free space link to a drone to verify sub-systems required in communication between the ground station and a spacecraft in cis-Lunar space. Accomplishing this verification of the telescope pointing systems and communications systems would have otherwise been much harder or impossible without using a retroreflected drone link. Full article
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<p>(<b>a</b>) Optical terminal. The upper-right box contains the free-space optics and machine vision system. The lower-left box is a tip-tilt mirror high voltage stage. The upper-left telescope is from an unrelated system. (<b>b</b>) Drone carrying the optical payload. Inset: close-up of the optical payload, consisting of LED array, pilot camera and corner-cube retroreflector.</p>
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<p>Schematic of the free-space optical pulse-position modulation demonstration. CCR: corner-cube retroreflector; FFC: fibre-to-free-space collimator; FPGA: field programmable gate array; GBE: Galilean beam expander; PD: photodetector; PID: proportional, integral, derivative; SWIR: short-wave infrared; VOA: variable optical attenuator.</p>
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<p>Bit-error rate versus signal-to-noise ratio (SNR) of 720 received 15120 bit 4-PPM codewords.</p>
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7 pages, 359 KiB  
Brief Report
A Lunar Backup Record of Humanity
by Carson Ezell, Alexandre Lazarian and Abraham Loeb
Signals 2022, 3(4), 823-829; https://doi.org/10.3390/signals3040049 - 7 Nov 2022
Viewed by 1988
Abstract
The risk of a catastrophic or existential disaster for our civilization is increasing this century. A significant motivation for a near-term space settlement is the opportunity to safeguard civilization in the event of a planetary-scale disaster. A catastrophic event could destroy the significant [...] Read more.
The risk of a catastrophic or existential disaster for our civilization is increasing this century. A significant motivation for a near-term space settlement is the opportunity to safeguard civilization in the event of a planetary-scale disaster. A catastrophic event could destroy the significant cultural, scientific, and technological progress on Earth. However, early space settlements can preserve records of human activity by maintaining a backup data storage system. The backup can also store information about the events leading up to the disaster. The system would improve the ability of early space settlers to recover our civilization after collapse. We show that advances in laser communications and data storage enable the development of a data storage system on the lunar surface with a sufficient uplink data rate and storage capacity to preserve valuable information about the achievements of our civilization and the chronology of the disaster. Full article
(This article belongs to the Special Issue Enabling a More Prosperous Space Era: A Signal Processing Perspective)
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<p>Projected data rate for new content given historical growth rates.</p>
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<p>Maximum bandwidth of previous and planned NASA laser communications demonstrations [<xref ref-type="bibr" rid="B33-signals-03-00049">33</xref>].</p>
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19 pages, 16463 KiB  
Article
Molecular Collective Response and Dynamical Symmetry Properties in Biopotentials of Superior Plants: Experimental Observations and Quantum Field Theory Modeling
by Alessandro Chiolerio, Mohammad Mahdi Dehshibi, Giuseppe Vitiello and Andrew Adamatzky
Symmetry 2022, 14(9), 1792; https://doi.org/10.3390/sym14091792 - 29 Aug 2022
Cited by 3 | Viewed by 4925
Abstract
Trees employ impulses of electrical activity to coordinate actions of their bodies and long-distance communication. There are indications that the vascular system might act as a network of pathways for traveling electrical impulses. A question arises about the correlation and interplay between the [...] Read more.
Trees employ impulses of electrical activity to coordinate actions of their bodies and long-distance communication. There are indications that the vascular system might act as a network of pathways for traveling electrical impulses. A question arises about the correlation and interplay between the molecular (microscopic) level and the macroscopic observable behavior of the system (the electrical impulses), for individual trees and as a component of the larger living ecosystem, the forest. Results from the “Cyberforest Experiment” in the Paneveggio forest (Valle di Fiemme, Trento, Italy) are presented. It is shown that: (i) biopotential features of xylem biomolecular activity can be correlated with the solar (and lunar) cycle, (ii) tree stubs show an electrical molecular activity that is correlated with that of neighboring trees, (iii) statistical features of spike-like peaks and entropy can be correlated with corresponding thermal entropy, and (iv) basic symmetries of the quantum field theory dynamics are responsible for the entanglement phenomenon in the molecular interactions resulting in the molecular collective behavior of the forest. Findings suggest implementing technology that goes in the direction of understanding the language of trees, eventually of fungi, which have created a universal living network perhaps using a common language. Full article
(This article belongs to the Special Issue Recent Advance in Molecular and Cellular Biology)
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<p><b>Top</b> image: area of the installation in Paneveggio (TN, Italy) seen from a patchwork of camera shots. <b>Bottom</b>, from left to right: map showing the exact location of the experiment, indicated by the red circle (diameter corresponding to 100 m); detail showing the geometry of the electrodes inserted in a <span class="html-italic">Picea abies</span> tree of approximately 70 years of age, labeled with Greek letters; detail about the box hosting PV modules, battery for powering the infrastructure and WiFi router for collection and data relay, during installation.</p>
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<p>Data measured from site D, tree D1, over ten individual electrodes. Four magnification steps are shown.</p>
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<p>Data measured from site B, tree B2, over ten individual electrodes. Two magnification steps are shown, including the Fast Fourier Transform analysis as Total Impulse Square Amplitude and the Short Time Fourier Transform map.</p>
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<p>Data measured from site D, tree D1, over ten individual electrodes during the autumn equinox, with full moon and clear sky.</p>
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<p><b>Top left</b>: number of spikes, barcode entropy, Simpson index, space filling, Kolmogorov entropy, signal entropy, expressiveness, Tsallis entropy, and Renyi entropy for a selected channel of a selected tree of a selected site. <b>Top right</b>: number of spikes for a selected channel of a selected tree of a selected site. <b>Bottom</b>, from left to right: Kolmogorov entropy of two selected channels of a selected tree of a selected site, Signal entropy of two selected channels of a selected tree of a selected site.</p>
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<p><b>Top row</b>: histograms of the population of spike-like structures detected on different sites. <b>Bottom row</b>, left: FFT map of a selected channel. Right: two-dimensional map of the Kolmogorov entropy over the site populated by stubs. Symbols identify correlated stubs, dashed lines separate the couple of electrodes that work together in differential mode.</p>
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<p><b>Top</b>: qualitative matching between Kolmogorov entropy computed from the biopotential signal, averaged over the electrodes of site B, and Shannon entropy computed from the thermographies shown in the right panel, shot from the same site B. <b>Bottom</b>: thermographies of a <span class="html-italic">Picea abies</span> trunk approximately 100 years old in site B (panels <b>a</b>–<b>f</b>) and algebraic difference between the registered frames above, which better allows noticing changes in temperature distribution (panels <b>g</b>–<b>k</b>).</p>
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<p>Artist view of the future measurements on the underground Wood Wide Web to map the network geometry by means of electrical tomography.</p>
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<p>Electronic characterization of several resins: <span class="html-italic">Picea abies</span>, <span class="html-italic">Cedrus deodara</span>, and <span class="html-italic">Larix decidua</span>. <b>Top row</b>: impedance measurements, showing resistive (left) and reactive (right) components. <b>Bottom row</b>: high voltage range behavior of the <span class="html-italic">Picea abies</span> resin (left), and extrapolated linear fit parameters in a comparison between all the three resins (right).</p>
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