Satellite Structure Research Articles

Space exposure test of hardwood specimens in the International Space Station

To design a wooden satellite and select the appropriate wood species, we conducted a space exposure test of wood on the International Space Station (ISS). The space exposure test used the Japanese Experiment Module “Kibo” on the Exposed Experiment Bracket Attached on i-SEEP (ExBAS), which is connected to the exposed facility of the ISS. Three wood species considered candidates for the structure of a wooden satellite were used in the exposure test: honoki (Magnolia obovata), yamazakura (Cerasus jamasakura), and dakekanba (Betula ermanii). In the outgassing test conducted in preparation for the space exposure test, the collected volatile condensable materials (CVCM) of the three wood species were below the critical value; however, the total mass loss (TML) exceeded the critical value. However, this was not a problem, because most of the mass loss was due to water evaporation. A space exposure test was conducted for 10 months in 2022. Consequently, no change was observed in the weight of the exposed specimen, and no erosion due to atomic oxygen (AO) was observed. The exposure test was scheduled to be carried out in the forward direction of the ISS travel; however, owing to equipment trouble, it was installed in the opposite direction. This is because an insufficient AO flux collided with the specimen. In terms of wood color, the brightness of the three species decreased owing to space exposure, and saturation increased in two wood species, except for yamazakura. A thin-film layer was observed on the surface of the aluminum cover to which the exposed specimen was fixed, which may have also formed on the surface of the wood specimen, reducing its brightness. However, because the hue angle did not change significantly, only a slight deterioration of the surface layer owing to vacuum ultraviolet was observed. The results confirmed that the wood had hardly deteriorated in space for approximately 10 months.

Optimization of embedded sensor placement for small satellites

Abstract Dynamic environment testing is important in the manufacturing phase of a satellite before launch. However, redundancy is introduced into the testing by the massive placement of vibration sensors inside and outside the satellite, adversely affecting testing efficiency, especially in the development of satellite constellations. An intelligent algorithm-based sensor optimization method is proposed to maximize the relationship between measure points and reduce the number of internal sensors while ensuring the independence of external sensors. A frequency response matrix of internal and external sensors is constructed through a frequency-sweeping analysis of the satellite structure. Subsequently, external sensors are categorized into different groups by using principal component analysis (PCA) and K-means clustering analysis. A modified information entropy approach is applied to optimize the quantity of internal sensors. Through the practical application of sensor reduction in a specific satellite, the proposed method achieves a good reduction result.

The Share of Data in Maritime Communications is Increasing

Communication is of great importance for the safe and delay-free navigation of ships. Especially life/property safety, navigational warnings, weather forecast reports, storm warnings, navigation maps, etc. Timely transmission of information to ships is only possible with effective maritime communications. In addition, communication is of great importance in making appropriate navigation plans based on the information received from the ships. In recent years, the share of data communication in individual and corporate communications has been increasing. In order to benefit from the great conveniences and opportunities provided by data communication in maritime communication systems, very radical decisions have recently been taken within IMO. These regulations made at the international level paved the way for data communication in close-range maritime communication systems. In line with these regulations, broadband data communication between the ship and the land will begin to be made via VHF devices in the next few years. Another development that will improve broadband data communication in maritime communication systems has been in Near Orbit Satellite systems. The technical features of these systems, the number of which has been increasing in recent years, are extremely suitable for data communication between ship and land. Among these, the Starlink system completes its network in space faster than other satellite systems. It is inevitable that the Starlink system, whose global satellite structure will be completed to a large extent by the end of 2025, will be used to a large extent in data communication between ships and land and between ships with each other. With the use of broadband data feature in the near future, it will be possible for ships to navigate much more safely, efficiently and with a reduced risk of accidents. For this purpose, maritime enterprises, ship personnel and land units must be informed about these developments and their communication infrastructure must be established by taking these systems into consideration.

Identifying Crop Distress and Stress-Induced Plant Diseases Using Hyper Spectral Image Analysis

The purpose of this study is to determine whether hyper spectral images can be used to identify plant diseases and crop pressure from aerial photographs. With extensive research on the prevalent methods used closer to the problem, this study offers a potent strategy for identifying crop distress and illnesses using this efficient imaging technique. To identify the spectral fingerprints of common indications and symptoms of plant diseases and crop strains, this study evaluates the available hyper spectral photo datasets. After that, the data are examined using two learning algorithms—the highly randomized trees and the Random Woodland set of rules—to create predictions that are entirely dependent on the results that are discovered. In the end, a benchmarked set of test statistics is used to assess the prediction accuracy. The results of this study show that hyper spectral photo evaluation has a strong and promising utility for crop stress and disease identification. Hyper spectral light evaluation is a method for identifying plant diseases caused by strain on crops. By gathering and evaluating high-dimensional spectral reflection data from satellite or aircraft structures, details regarding the physiological homes of flowers can be identified. The health of plants, illnesses brought on by stress, and agricultural productivity predictions can all be made using these facts. Hyper spectral recordings can also be used to create actions that reduce agricultural losses and enhance the health of plants that are prone to disease.

Highly Stable Carboranyl Ligated Gold Nano-Catalysts for Regioselective Aromatic Bromination.

Achieving electronic/steric control and realizing selectivity regulation in nanocatalysis remains a formidable challenge, as the dynamic nature of metal-ligand interfaces, including dissolution (metal leaching) and structural reconstruction, poses significant obstacles. Herein, we disclose carboranyls (CBs) as unprecedented carbon-bonded functional ligands (Eads.CB-Au(111)=-2.90 eV) for gold nanoparticles (AuNPs), showcasing their exceptional stabilization capability that is attributed by strong Au-C bonds combined with B-H⋅⋅⋅Au interactions. The synthesized CB@AuNPs exhibit core(Aun)-satellite(CB2Au-) structure, showing high stability towards multiple stimuli (110 °C, pH=1-12, thiol etchants). In addition, different from conventional AuNP catalysts such as triphenylphosphine (PPh3) stabilized AuNPs, dissolution of catalytically active gold species was suppressed in CB@AuNPs under the reaction conditions. Leveraging these distinct features, CB@AuNPs realized outstanding p : o selectivities in aromatic bromination. Unbiased arenes including chlorobenzene (up to >30 : 1), bromobenzene (15 : 1) and phenyl acrylate were examined using CB@AuNPs as catalysts to afford highly-selective p-products. Both carboranyl ligands and carboranyl derived counterions are crucial for such regioselective transformation. This work has provided valuable insights for AuNPs in realizing diverse regioselective transformations.

Proposing novel body-centered cubic lattice core sandwich panels as satellite structure

In the present paper, a comparative study on the load-bearing as well as shielding performance against hypervelocity impact of space debris of sandwich panels with body-centered cubic lattice core is performed numerically in order to evaluate their eligibility to be utilized as the satellite structure. To this end, four types of body-centered cubic lattice structures, with similar areal densities which are assumed to be made of 5A06 aluminum alloy, including BCC, BCCz (BCC reinforced in Z direction), and also BCCz-I and BCCz-II were considered. Whipple shield structure of same material and areal density was also investigated in order to justify the necessity of lattice structures application, especially in protection field. The present study simulates hypervelocity impact of a spherical projectile with 2 mm diameter, represented the space debris, collides with the structures at the velocity range of 2–6 km/s. Current numerical simulation process accuracy and efficiency were verified through comparing its obtained data based on simulating a problem had been investigated at a valid experimental study to the data proposed by the mentioned research. BCCz-II structure which is newly proposed at this study provided outstanding shielding and load-bearing capabilities in comparison to other structures. Furthermore, the detailed effects of projectile impact location and a middle structure placed plate on the protection performance were investigated and the mentioned items were found to have crucial impact on the structure shielding performance.

Antena Dwi Port Dwi Pengutuban Bulat terinspirasi Bahan Meta untuk Sistem Komunikasi Satelit Kecil

This paper presents a dual circular polarized C-band patch antenna for a small satellite communication system The antenna consists of two different annular patch structure with three split ring resonators. The antenna is designed considering space environment and the smallest form of satellite structure. The antenna is fabricated space qualified substrate material Rogers 5880 with overall dimension of 85.22× 48.59 × 1.575 mm3. The antenna achieves circular polarization at 5.1 GHz and 5.2 GHz frequency for port 2 and port 1, respectively. The split ring resonator structures contribute to enhance antenna gain and axial beamwidth. Realized gain of 7.29 dB and 7.33 dB are achieved at 5.1 GHz and 5.2 GHz operating frequency with 3dB axial beamwidth of 170 ̊ and 153 ̊ , respectively. Antenna size and performance show that the antenna can be a potential candidate for smooth operation of small satellite communication system.

Evaluating load-bearing and hypervelocity impact shielding capabilities of face-centered cubic lattice core sandwich panels

In the present paper, a comparative study on load-bearing as well as hypervelocity impact shielding performance of sandwich panels with face-centered cubic (FCC) lattice core is numerically performed in order to evaluate their competency in satellite structure applications. To this end, 5A06 aluminum alloy FCC and FCCz beside cube and octahedron lattice structures with similar areal densities were investigated. Whipple shield structure of same material and areal density was also studied in order to be compared to lattice structure in protection field. The present study simulates hypervelocity impact of a spherical projectile with 2 mm diameter, represents the space debris, collides with the structures at the velocity range of 2–6 km/s. Numerical simulation model was validated by performed experimental study. Authors were inspired by cube and FCCz topologies to propose a novel lattice structure could provide outstanding shielding and load-bearing capabilities in comparison to the other structures studied in this research. Furthermore, the detailed effects of projectile impact location on the protection performance were investigated and the mentioned item was found to have considerable influence on the structure shielding performance.

P-262 Clinical viability of oocytes with micronuclei at fertilisation

Abstract Study question Does the presence of micronuclei at fertilisation impact on embryo potential? Summary answer Embryos displaying micronuclei at fertilisation exhibit decreased utilisation rates and lower euploidy rates, however are capable of resulting in clinical pregnancies. What is known already The appearance of two pronuclei defines normal fertilisation. With advances in imaging techniques, a range of pronuclei phenotypes can now be identified in more detail, including additional micronuclei. Micronuclei are smaller satellite structures appearing around the pronuclei. Previous studies have determined that embryos containing two primary pronuclei and one micronuclei are generally diploid and can develop to blastocyst stage. However, these studies were limited in sample size, did not have consistent imaging techniques and assessed only the presence or absence of micronuclei, not their size or number. Study design, size, duration Retrospective cohort analysis in a single, large IVF centre including all oocytes entering culture between January 2022 and December 2023 (n = 33,237). All embryos were cultured in Embryoscope+ using Vitrolife sequential media at 6% CO2 and 5% O2. ICSI and naturally inseminated oocytes were included. All embryos were cultured to day 5/6 before determining suitability for transfer, freezing and/or genetic testing. Participants/materials, setting, methods During routine daily annotation, embryologists assessed fertilised oocytes for the presence of micronuclei. This study re-examined all embryos annotated as displaying micronuclei and further assessed: number of micronuclei, their position (‘apposed’ or ‘distant’ from the pronuclei, and in the case of > 1 micronuclei ‘clustered’ or ‘spread’) along with the area (μm2) of the two largest micronuclei and area (μm2) of primary pronuclei using Embryoscope+ software. Clinical pregnancy was defined as presence of a gestational sac. Main results and the role of chance Micronuclei were observed in 0.45% (n = 149/33,237) of all oocytes assessed. The majority of these presented as one additional nuclei 92.60% (n = 138), 7.38% (n = 11) showed two additional nuclei and 0.67%(n = 1) had multiple (more than 2) micronuclei. All micronuclei appeared apposing a primary pronucleus. In the event of multiple micronuclei, 82% were clustered whereas 9% was spread throughout the around the primary pronuclei. The average area of the largest micronuclei in each oocyte was 80.33μm2 ± 26.81.The mean area of all micronuclei was 76.80μm2, approximately 16% of the size of primary pronuclei measured, 465.09μm2. The utilisation rates of embryos derived from micronuclei fertilisation were 28.18% (N = 42) compared to 49%, n = 4118 of 2PN derived embryos. All but one of these presented two primary pronuclei and one additional micronuclei, with the remaining embryo displaying two micronuclei. Twelve of these embryos were transferred (in a fresh stimulated cycle (n = 5) or a subsequent frozen embryo transfer cycle (n = 7), resulting in four clinical pregnancies, however only one ongoing clinical pregnancy. PGT testing was performed on 19 embryos, with only two, 6.67% returning a euploid results, 68.42% resulting an aneuploid, of the remaining four embryos, 2 achieved a mosaic result and 2 received a no result. Limitations, reasons for caution As the occurrence of micronuclei is rare, only a limited number of embryos were available for analysis. Furthermore, this study was conducted in a large single laboratory and can not account for differences in culture conditions between laboratories. Inter-operator variability among initial fertilisation annotations could not be excluded. Wider implications of the findings By creating a definition of the micronuclei measurement, it provides safeguard for micronuclei to be assessed in culture. The data presented here can help guide clinical decisions where micronuclei are present. Trial registration number not applicable

Iterative design of satellite structures and topology optimisation methods

Abstract Satellite launches are critical amid increasing demands for advanced services. Rising costs urge innovation in engineering. Enhancing satellite structural integrity during launches is crucial due to intense vibrations. Topology optimisation and additive manufacturing converge as promising solutions. Topology optimisation uses mathematical techniques to iteratively improve structures by reducing mass while enhancing attributes like load capacity. This field, active for about three decades, employs continuum and discrete algorithms to optimise structures. Recent trends show optimised structures through topology optimisation and additive manufacturing promise cost-effective and high-performance solutions. This study aims to extensively review topology optimisation methods, specifically focusing on satellite structures, to shape future developments within the years to come.

High-accuracy measurement, advanced theory and analysis of the evolution of satellite transitions in manganese Kα using XR-HERFD.

Here, the novel technique of extended-range high-energy-resolution fluorescence detection (XR-HERFD) has successfully observed the n = 2 satellite in manganese to a high accuracy. The significance of the satellite signature presented is many hundreds of standard errors and well beyond typical discovery levels of three to six standard errors. This satellite is a sensitive indicator for all manganese-containing materials in condensed matter. The uncertainty in the measurements has been defined, which clearly observes multiple peaks and structure indicative of complex physical quantum-mechanical processes. Theoretical calculations of energy eigenvalues, shake-off probability and Auger rates are also presented, which explain the origin of the satellite from physical n = 2 shake-off processes. The evolution in the intensity of this satellite is measured relative to the full Kα spectrum of manganese to investigate satellite structure, and therefore many-body processes, as a function of incident energy. Results demonstrate that the many-body reduction factor S02 should not be modelled with a constant value as is currently done. This work makes a significant contribution to the challenge of understanding many-body processes and interpreting HERFD or resonant inelastic X-ray scattering spectra in a quantitative manner.

Negative charge-transfer energy in SrFeO3 revisited with hard x-ray photoemission spectroscopy

We report hard x-ray photoelectron spectroscopy on SrFeO3 which is one of the classical conducting transition-metal oxides with a noncollinear magnetic structure. The obtained spectra show a detailed charge-transfer (CT) satellite structure, the Fe 2p3/2 main peak exhibits multiplet splitting, and the deterioration signs present in previous reports are absent here, allowing for a better determination of its intrinsic electronic structure. The results are well described by a FeO6 cluster model with a charge-transfer energy of about −1.0 eV, confirming the values obtained in the previous works. The negative CT energy indicates that the electronic configuration of the tetravalent Fe is d5L rather than d4 where L represents an O 2p hole. The small spectral weight observed at the Fermi level indicates the correlated metallic state with localized Fe 3d electrons and mobile O 2p holes which are governed by a large d−d Coulomb interaction and negative CT energy. Published by the American Physical Society 2024

A Simple Method for Identifying the Natural Frequency of a Micro Satellite with a Primary Structure Made of Aluminum Alloy

Microsatellites must survive severe mechanical conditions during their launch phase. Usually, the structural design of a micro satellite is performed using the internal stress analysis and the natural frequency analysis, which are based on a finite element method (FEM). The validity of this structural design is evaluated through vibration tests. In an early stage of development, which has a FEM model of a satellite in the process of creation, presumption of the minimum natural frequency of a satellite may be difficult. In this study, a simple method for determining the longitudinal and lateral minimum natural frequencies of microsatellites during the ascent phase was clarified. The structure of the microsatellites used in this research is made of aluminum alloy, and they have a monocoque structure. The Young’s modulus and moment of inertia of area used to calculate the minimum natural frequencies were determined using the area ratio of the monocoque structure to the entire satellite. When the method proposed in this study is used, the calculated values agree with the vibration-tested values within 10%. In particular, in the case of W6U-type satellites, the two agree within a range of approximately 2% in the longitudinal direction and approximately 5% in the lateral direction. In the early stages of a satellite structure design when a FEM cannot be created, the proposed method will work effectively as the method of determining the minimum natural frequency. In order to simplify the process of microsatellites development, this paper describes a practical estimation method of the minimum natural frequency for microsatellites.

Modal analysis of honeycomb panel satellite structure based on MSC Apex

Modal analysis plays an important role in the process of Satellite structure development. In this paper, the honeycomb sandwich plate and the satellite structure are taken as the research objects, and the corresponding finite element models are established. The analysis results of the actual modeling of honeycomb plate and the equivalent modeling of sandwich sandwich plate are obtained, and the fundamental frequency deviation of the whole satellite structure is discussed when the equivalent correction coefficient γ of honeycomb plate is different. The results show that the maximum relative error of the modal frequency between the equivalent method of sandwich sandwich plate and the actual modeling is 2.8%. Therefore, the equivalent method can be applied to large-scale finite element analysis and calculation, and the calculation efficiency can be improved. When the value of γ is 0.4∼0.6, the vibration modes of the whole satellite structure are basically consistent, and the maximum fundamental frequency difference is 10%. The results can evaluate the accuracy of the sandwich sandwich plate equivalent method for satellite mechanical analysis.

Experimental analysis of noise disturbances generated by reaction wheel

Abstract Microvibrations originating from onboard disturbance sources can lead to a range of issues, including a decrease in satellite pointing accuracy, image distortion and blurring. Therefore, reaction wheels emerge as the primary sources of disturbance noise. This paper employs an experimental approach based on the real dynamics of rotating reaction wheel assembly, closely simulating on-orbit configurations to measure noise responses transferred to the satellite structure. An assessment of noise response behaviour, incorporating a comprehensive understanding of the factors influencing the levels, was conducted on a proto-flight satellite for three reaction wheels. Initially, reaction wheel assemblies underwent individual iterative balancing to reduce mass deviations. Subsequently, amplitude-time responses at different rotational speeds of reaction wheel assemblies (RWA) disturbance noise were measured. The experimental results demonstrate that each individually balanced reaction wheel generates independent perturbation noise level due to manufacturing imperfections. Hence, the necessity of wheels testing for accurate prediction and mitigation of disturbance levels is crucial, especially for payloads sensitive to microvibrations. Furthermore, increasing wheel speeds proportionally amplify disturbance noise levels. Therefore, implementing an optimised mission attitude control profile with lower rotation speeds of reaction wheels effectively reduces microvibration levels which minimises risks to payload performance and reduce power consumption.

Assembly deviation analysis of satellite flexible parts integrating rigid and flexible properties: Modeling and experiment

With the advancement of space technology, satellites are assuming an increasingly pivotal role in various fields. Currently, satellite structures incorporate a growing number of thin-walled parts. During the assembly process, the movement and connection of these parts are prone to generating assembly deviations, which seriously affects the overall assembly quality of the satellites. In order to accurately predict assembly deviations before assembly, this paper introduced an assembly deviation analysis model which took rigid and flexible properties into account. Starting from the attitude adjustment of satellite assembly, the transmission law of manufacturing error was established. Then, the assembly deviation analysis model integrating rigid and flexible properties was established. Finally, the assembly experiment was carried out to verify the effectiveness of the proposed model. The results showed that the average absolute error between the measurement results and calculation results was only 0.032 mm and the maximum absolute error was 0.074 mm. The average solving accuracy of the assembly deviation was 94%. The result fully proved the effectiveness of the proposed model.

Proposal for a realtime Einstein-synchronization-defined satellite virtual clock

Abstract The realization of high performance satellite onboard clock is vital for various PNT applications. For further improvement of the synchronization-based satellite time and frequency references, this paper proposes a geosynchronous (GEO) satellite virtual clock concept based on ground–satellite synchronization and presents a beacon transponder structure for its implementation (scheduled for launch in 2025), which does not require atomic clocks to be mounted on the satellite. Its high performance relies only on minor modifications to the existing transponder structure of GEO satellites. We carefully modeled the carrier phase link and analyzed the factors causing link asymmetry within the special relativity. Considering that the performance of such synchronization-based satellite clocks is primarily limited by the link’s random phase noise, which cannot be adequately modeled, we designed a closed-loop experiment based on commercial GEO satellites for pre-evaluation. This experiment was aimed at extracting the zero-means random part of the ground-satellite Ku-band carrier phase via a feedback loop. Ultimately, we obtained a 1σ value of 0.633 ps (two-way link), following the Gaussian distribution. From this result, we conclude that the proposed real-time Einstein-synchronization-defined satellite virtual clock can achieve picosecond-level replication of onboard time and frequency.

Digital twin-driven assembly accuracy prediction method for high performance precision assembly of complex products

The high performance precision assembly (HPPA) of complex products such as aerospace, aircraft and high-end machine tool has demanding requirements for assembly accuracy. Achieving the accurate prediction of assembly accuracy for these complex products before assembling is the premise of improving the assembly quality and performance, and also has always been a challenge. Existing assembly accuracy prediction methods focus on acquiring the assembly deviation based on CAD model and manufacturing errors of parts, but rarely involve the multidimensional error coupling of parts and the influencing factors in the assembly process, which inevitably cause a certain gap between the prediction result and the actual condition, affecting the reliability of the prediction result. To address the above problems, this paper presents a digital twin (DT)-driven assembly accuracy prediction method for the HPPA of complex products. Firstly, this paper introduces the methodology overview and proposes an overall framework for DT-driven assembly accuracy prediction. Secondly, three key enabling technologies realizing the DT-driven assembly accuracy prediction, including the construction of part digital twin model, the generation of DT-based assembly process model, and assembly deviation propagation and accuracy analysis are introduced in detail. Finally, an application implementation of a prototype system and a case study involving a simplified satellite structure panel assembly process are used to verify the effectiveness and feasibility of the proposed method.

Structure of native four-repeat satellite III sequence with non-canonical base interactions.

Tandem-repetitive DNA (where two or more DNA bases are repeated numerous times) can adopt non-canonical secondary structures. Many of these structures are implicated in important biological processes. Human Satellite III (HSat3) is enriched for tandem repeats of the sequence ATGGA and is located in pericentromeric heterochromatin in many human chromosomes. Here, we investigate the secondary structure of the four-repeat HSat3 sequence 5'-ATGGAATGGA ATGGA ATGGA-3' using X-ray crystallography, NMR, and biophysical methods. Circular dichroism spectroscopy, thermal stability, native PAGE, and analytical ultracentrifugation indicate that this sequence folds into a monomolecular hairpin with non-canonical base pairing and B-DNA characteristics at concentrations below 0.9 mM. NMR studies at 0.05-0.5 mM indicate that the hairpin is likely folded-over into a compact structure with high dynamics. Crystallographic studies at 2.5 mM reveal an antiparallel self-complementary duplex with the same base pairing as in the hairpin, extended into an infinite polymer. The non-canonical base pairing includes a G-G intercalation sandwiched by sheared A-G base pairs, leading to a cross-strand four guanine stack, so called guanine zipper. The guanine zippers are spaced throughout the structure by A-T/T-A base pairs. Our findings lend further insight into recurring structural motifs associated with the HSat3 and their potential biological functions.

Effects of microgravity and reduced atmospheric pressure on manufacturing photopolymer specimens

In-space manufacturing especially for external satellite structures has a huge potential to increase the packaging density of a satellite in launch configuration and enables large structures for advanced mission requirements. However, the processes and materials do have to withstand the harsh environmental conditions in space. These conditions have immediate effects on the manufacturing process as well as long-term effects on the structure manufactured in orbit. The experiments presented here are based on a photopolymer extrusion process by UV-radiation curing that is intended to be used as an in-space manufacturing technology. In order to understand the influence of reduced atmospheric pressure and microgravity on the process, we demonstrated the successful extrusion and curing of rod-shaped elements during a sounding rocket flight. Simultaneously, the same experiment was performed on the ground under normal gravity and ambient pressure. By comparing both groups of specimens, it was shown that the morphological artifacts and geometric deviations are more significant for the specimens manufactured during flight. This evaluation was performed by visual inspection, by comparison of the laser-scanned specimens with a reference model and by measuring and comparing the mass, length and diameter of the specimens. On a microscopic level, conducted by computer tomography, no influence of the reduced atmospheric pressure on the extrusion of the liquid photopolymer can be recognized as this was probably not low enough at the altitude reached by the rocket. As a result of this article, measures are proposed to avoid the morphological artifacts observed during the experiments and thus achieve higher accuracy and a resilient in-space manufacturing process.