본 자료는 우주 탐사, 우주비행사, 우주선, 우주 유영 활동, 발사체, 우주 정거장, 테라포밍, 소행성대, 달 착륙선, 우주 탐사선, 화성 탐사 로버, 우주 망원경, 무중력, 성간 여행, 우주생물학, 외계 행성 등 다양한 주제를 다루는 전 세계 영어 출판물 및 특허를 엄선하여 정리한 최신 자료입니다.
Micromanufacturing and bioprinting cartridge in a micro gravity environment
Patent published on the 2026-10-15 in WO under Ref WO2026217648 by AUXILIUM BIOTECHNOLOGIES INC [US] (Lazarovits Isac [us], Necessary Chess [us], Varnado Paul [us])
Abstract: The system, methods, and uses of three-dimensional micromanufacturing materials, scaffolds, and living tissues in microgravity environment that is found in space such as Low-Earth-Orbit, on a spacecraft in-transit between celestial bodies, or on other celestial bodies such as the Moon or Mars.[...]
Our summary: This content discusses micromanufacturing and bioprinting techniques for creating materials and living tissues in microgravity. It highlights the applications of these technologies in space environments like Low-Earth-Orbit and on celestial bodies. The focus is on the development of scaffolds for three-dimensional structures in these unique conditions.
Micromanufacturing, bioprinting, microgravity, scaffolds
Patent
Thermal regulation of high power spacecraft electronics via encapsulation in phase change material
Patent published on the 2026-10-08 in US under Ref US20260313861 by STARCLOUD INC [US] (Oltean Paul Adrian [us], Feilden Ezra [gb], Johnston Philip [us])
Abstract: This disclosure relates to a local thermal regulation solution for high-power electronics or printed circuit assemblies for use onboard satellites. Thermal regulation is achieved by immersing electronic components in a dielectric phase change material (PCM) within an encapsulating hermetically sealed enclosure. The dielectric PCM can absorb transient thermal spikes during intermittent high-power operations then release this stored energy during low points in the duty cycle. The released thermal [...]
Our summary: This disclosure presents a thermal regulation solution for high-power electronics in satellites. It involves encapsulating components in a dielectric phase change material to manage thermal spikes and energy release. An integrated expansion relief mechanism ensures optimal heat absorption and compensates for volumetric changes during phase transitions.
Thermal regulation, phase change material, spacecraft electronics, encapsulation
Patent
Spacecraft liquid transport system
Patent published on the 2026-10-08 in US under Ref US20260307822 by SPACE OCEAN CORP [US] (Fuchs Alden [us], Keppler Sean David [us], Mcginn Charles [us], Foy Aidan [us], Kundrapu Madhusudhan N [us], Vasquez Diego [us], Williams Christopher [us], Uribe Brendan [us])
Abstract: [0000] In one embodiment, a system for transporting a liquid in space comprises one or more expandable containers configured to store a liquid, wherein each container comprises a flexible, collapsible material. The system further comprises a pressure control system in mechanical communication with the container. The pressure control system is configured to apply an external force to maintain an internal pressure sufficient to keep the liquid in a liquid state in a vacuum environment. The system [...]
Our summary: The system uses expandable containers made of flexible material to store liquids in space. A pressure control system maintains the necessary internal pressure to keep the liquid from vaporizing. A fluid transport assembly allows for controlled intake and dispensing of the liquid.
liquid transport, expandable containers, pressure control, fluid assembly
Patent
Section of a spacecraft and method for re-entry
Patent published on the 2026-09-30 in EP under Ref EP4813845 by ARIANEGROUP GMBH [DE] (Goek Sylvain [de])
Abstract: Disclosed are a section of a spacecraft having at least a lower part such as a propulsion module and an upper part such as a payload fairing, wherein the parts are adapted to be moved telescopically into one another after a payload has been released into orbit, and a method for preparation of this section for re-entry.[...]
Our summary: The invention describes a spacecraft section with a propulsion module and a payload fairing. The parts can move telescopically after payload release. A method for preparing this section for re-entry is also disclosed.
spacecraft, re-entry, propulsion module, payload fairing
Patent
Method to determine a position, velocity and timing solution of a spacecraft or satellite, satellite or spacecraft and use of a receiver
Patent published on the 2026-09-30 in EP under Ref EP4814544 by SPACEOPAL GMBH [DE] (Bauerhin AndrÉ [de])
Abstract: [0001] A method to determine a position of a mobile receiver in a global navigation satellite system (GNSS), comprising - receiving primary global navigation signals at a receiver of a satellite, - receiving correction and bias data via a first communication channel at the receiver of the satellite, - determining an orbit position of the satellite based on the primary global navigation signals and the correction and bias data by precise point positioning (PPP), - creating a secondary global navi[...]
Our summary: The method involves receiving primary navigation signals and correction data at a satellite. It determines the satellite s orbit position using precise point positioning. A secondary navigation signal is then created and broadcasted to a mobile receiver for position determination.
GNSS, precise point positioning, satellite communication, orbit determination
Patent
Kinetic capture of orbital debris
Patent published on the 2026-09-10 in US under Ref US20260264886 by BLUE ORIGIN MFG LLC [US] (Agnew Jonathan [us])
Abstract: [0000] Systems, devices, and methods for kinetically capturing orbital debris. The system actively seeks and captures debris in orbit and serves as a payload adaptor. The system releasably supports the payload on a rocket. The system releases the payload and then separates from the rocket and inserts into a debris collision orbit. The system may include thrusters and a flight control system. The system includes an impact structure that deforms upon impact and retains therein the debris. The syst[...]
Our summary: The system captures orbital debris using kinetic methods. It includes a payload adaptor that supports and releases payloads from rockets. The impact structure deforms to retain captured debris, utilizing a metal foam composite for effective impact absorption.
Kinetic capture, orbital debris, payload adaptor, impact structure
Patent
Coverage Ratio–Based Evaluation of Antenna Omnidirectionality for a Pair of Microstrip Patch Antennas on a 6U CubeSat
Published on 2026-02-03 by Daisuke Nakayama, Kei Sano, Rin Sato, Tohlu Matsushima, Yuki Fukumoto @MDPI
Abstract: CubeSat missions increasingly rely on microwave-band communication systems, whose antennas often exhibit directional radiation patterns. As a result, multiple antennas are commonly used to improve coverage; however, a quantitative method to evaluate their performance across all spacecraft attitudes has been lacking. This paper introduces the Coverage Ratio of CubeSat Attitude (CRCA), a metric that quantifies the proportion of orientations for which the antenna gain exceeds a required threshold. [...]
Our summary: This paper presents the Coverage Ratio of CubeSat Attitude (CRCA) metric to evaluate antenna performance across spacecraft orientations. It demonstrates the CRCA using the S-band command antenna system of the 6U CubeSat VERTECS. The study compares antenna configurations and shows the effectiveness of the proposed metric in assessing communication performance under varying attitudes.
Coverage Ratio, Antenna Omnidirectionality, CubeSat, Microwave Communication
Publication
A Multi-Modal Decision-Level Fusion Framework for Hypervelocity Impact Damage Classification in Spacecraft
Published on 2026-02-02 by Kuo Zhang, Chun Yin, Pengju Kuang, Xuegang Huang, Xiao Peng @MDPI
Abstract: During on-orbit service, spacecraft are subjected to hypervelocity impacts (HVIs) from micrometeoroids and space debris, causing diverse damage types that challenge structural health assessment. Unimodal approaches often struggle with similar damage patterns due to mechanical noise and imaging distance variations. To overcome these physical limitations, this study proposes a physics-informed multimodal fusion framework. Innovatively, we integrate a distance-aware infrared enhancement strategy wi[...]
Our summary: This study presents a multi-modal fusion framework for classifying hypervelocity impact damage in spacecraft. It integrates infrared enhancement and vibration spectral subtraction to improve data alignment. The approach achieves over 99% accuracy, significantly enhancing damage assessment precision and stability.
Multi-Modal Fusion, Hypervelocity Impacts, Structural Health Monitoring, Dempster-Shafer Theory
Publication
