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X-WR-CALNAME:International Moon Day
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X-WR-CALDESC:Events for International Moon Day
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TZID:Asia/Riyadh
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TZOFFSETFROM:+0300
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DTSTART:20240101T000000
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DTSTART;TZID=Asia/Riyadh:20250719T170000
DTEND;TZID=Asia/Riyadh:20250719T180000
DTSTAMP:20260421T131351
CREATED:20250714T080302Z
LAST-MODIFIED:20250718T212843Z
UID:10000224-1752944400-1752948000@internationalmoonday.org
SUMMARY:Space drones round trips to the moon: how are they possible?
DESCRIPTION:A science and technology presentation by the founder and CEO of Gaseous electronics LLC (www.gaselco.com). Riyadh\, Saudi Arabia.———AbstractThis presentation assesses the technical viability of a multi-stage propulsion concept for a 15-meter drone undertaking a lunar mission. The proposed architecture sequentially employs solid fuel for Low Earth Orbit (LEO) insertion\, an air-breathing engine for LEO-to-vacuum transition\, and a vacuum-optimized plasma thruster for trans-lunar cruise. Analysis indicates that while solid fuel propulsion is a mature and feasible solution for initial LEO insertion\, capable of delivering drone-scale payloads (e.g.\, 4-500 kg) \, the subsequent air-breathing engine stage presents a critical functional mismatch. Current Air-Breathing Electric Propulsion (ABEP) systems are designed for milli-Newton thrust levels (e.g.\, 6 mN) to compensate for atmospheric drag in Very Low Earth Orbit (VLEO) (120-250 km altitude)\, not to provide the substantial delta-V (3.2-3.6 km/s)  required for a rapid “kick” into vacuum or Trans-Lunar Injection (TLI). This inherent low-thrust characteristic renders ABEP unsuitable for orbital escape maneuvers. Conversely\, vacuum-optimized plasma thrusters (e.g.\, Ion\, Hall Effect\, VASIMR) are highly efficient for long-duration trans-lunar cruising\, achieving high specific impulse (2\,000-12\,000 s) with low thrust (mN to few N)\, leading to travel times of several months. However\, these systems demand continuous\, high-power electrical input (kW to MW range)\, necessitating significant advancements in compact\, high-power density energy sources and robust thermal management systems for drone integration. The overall concept’s viability is currently limited by the fundamental inability of proposed plasma technologies to provide high impulsive thrust for orbital escape and the substantial mass/complexity of required power infrastructure.
URL:https://internationalmoonday.org/event/space-drones-round-trips-to-the-moon-how-are-they-possible/
LOCATION:Riyadh\, Saudi Arabia\, Saudi Arabia
CATEGORIES:Online
ATTACH;FMTTYPE=image/png:https://internationalmoonday.org/wp-content/uploads/2025/07/Gaselco-modified.png
ORGANIZER;CN="Gaseous electronics LLC":MAILTO:amhala@gaselco.com
GEO:24.712160563211;46.671983564158
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DTSTART;TZID=Asia/Tokyo:20250720T140000
DTEND;TZID=Asia/Tokyo:20250720T150000
DTSTAMP:20260421T131351
CREATED:20250718T112602Z
LAST-MODIFIED:20250718T112603Z
UID:10000240-1753020000-1753023600@internationalmoonday.org
SUMMARY:ISU SSP25 Sustainable Lunar Infrastructure Team Project Discussion
DESCRIPTION:“What will enable large scale lunar activity?” \nAn online zoom meeting discussion with participants in the ISU SSP25 team project on Sustainable Lunar Infrastructure. This is the early phase of the ISU team project. This is an opportunity for an online discussion of some preliminary ideas. \n1. Eric Dahlstrom and Madhu Thangavelu introduce the Lunar Infrastructure team project. (5 min)\n2. Several participants discuss some of their initial ideas about the project. (20 min)\n3. Open discussion among people online. (30 min)
URL:https://internationalmoonday.org/event/isu-ssp25-sustainable-lunar-infrastructure-team-project-discussion/
LOCATION:Hanyang University ERICA campus\, South Korea\, 55 Hanyangdaehak-ro\, Sangnok-gu\, Gyeonggi-do\, Korea\, Republic of
CATEGORIES:Online
ATTACH;FMTTYPE=image/jpeg:https://internationalmoonday.org/wp-content/uploads/2025/07/ISU-SSP25.jpeg
ORGANIZER;CN="ISU":MAILTO:eric.dahlstrom@community.isunet.edu
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