In Situ Measurement of Carbon Fibre/Polyether Ether Ketone Thermal Expansion in Low Earth Orbit

Abdullah, Farhan; Okuyama, Keiichi; Fajardo, Isai; Urakami, Naoya

doi:10.3390/aerospace7040035

Cited by 12 publications

(11 citation statements)

References 20 publications

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“…The results show that it is possible to observe the CTE in a space environment and that material degradation can be observed in real time by measuring the CTE. The PEEK/CFRTP materials were not degraded after 120 days in space [12,13].…”

Section: Materials Mission Observation Resultsmentioning

confidence: 96%

“…The Ten-Koh 2 Material Mission uses the CTE of material degradation to make observations. The calculation of the CTE is based on the following equation [13]:…”

Section: Observation Methodsmentioning

confidence: 99%

“…It was launched into a Sun-synchronous sub-recurrent orbit at an altitude of about 600 km using the H-IIA rocket F40 in October 2018 as a sub-payload to JAXA's Greenhouse gases Observing Satellite-2 (GOSAT-2). Ten-Koh's Flight Model (FM) is shown in Figure 1 [12,13].…”

Section: Ten-kohmentioning

confidence: 99%

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The Thermo-Mechanical Properties of Carbon-Fiber-Reinforced Polymer Composites Exposed to a Low Earth Orbit Environment

Nishihara,

Okuyama,

Rodriguez

et al. 2024

Aerospace

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In this study, we focus on 3D-printed PEEK/CFRTP (Carbon-Fiber-Reinforced Thermoplastic) and PEEK (Polyether Ether Ketone) materials as new space materials. In space, there are intense ultraviolet (UV) rays that are weakened by the atmosphere on Earth, so it is essential to understand the degradation of materials due to UV rays in advance. Therefore, we developed a materials science experiment called the Material Mission, which will be carried out on board Ten-Koh 2. This mission measures the coefficient of thermal expansion (CTE) of the CFRTP samples and the PEEK samples in LEO without recovery. So, we developed a thermal expansion observation system to be installed on the Ten-Koh 2 satellite. In addition, UV irradiation tests simulating the UV environment in LEO were conducted as ground tests. From the results of the ground tests, it was possible to determine in advance the degree of degradation of each material in the UV environment, even up to 100 ESD. By utilizing these results in mission operations, more meaningful measurement results can be obtained, and this mission development can contribute greatly to developing new space materials in the future.

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Section: Materials Mission Observation Resultsmentioning

confidence: 96%

“…The Ten-Koh 2 Material Mission uses the CTE of material degradation to make observations. The calculation of the CTE is based on the following equation [13]:…”

Section: Observation Methodsmentioning

confidence: 99%

See 1 more Smart Citation

The Thermo-Mechanical Properties of Carbon-Fiber-Reinforced Polymer Composites Exposed to a Low Earth Orbit Environment

Nishihara,

Okuyama,

Rodriguez

et al. 2024

Aerospace

Self Cite

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show abstract

“…These conditions were independently examined before space utilization, for example [1][2][3] in the early stage of the research field. In recent studies, Abdullah et al 4 carried out in-situ measurements of changes in the coefficient of thermal expansion of carbon fiber/polyether ether ketone (CF/ PEEK) composites in a low Earth orbit under the Ten-Koh satellite project. Shimosako et al 5 examined the effects of atomic oxygen irradiation on anatasetype TiO 2 films.…”

Section: Introductionmentioning

confidence: 99%

Effects of electron beam irradiation on hypervelocity impact behavior of carbon fiber reinforced plastic plates

Nishida

Hongo

Takahara

et al. 2021

Journal of Composite Materials

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The effects of electron beam irradiation were examined on perforation holes and fragments from quasi-isotropic carbon fiber reinforced plastic plates (CFRP plates). CFRP plates with a total dose up to 60 MGy of electron beam irradiation were prepared for hypervelocity impact experiments. The perforation holes of CFRP plates in the hypervelocity impact experiments were decreased with electron beam irradiation when aluminum alloy spherical projectiles (2017-T4) of diameter of 1 mm struck at an impact velocity of 5 km/s. However, a slight reduction in the size of the perforation hole was observed at 2 km/s. Fragments ejected from CFRP plates were examined after collection from the impact side and rear side of the targets. The cumulative number distributions of fragment length and aspect ratio were compared among specimens with different total doses.

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“…The use of PEEK as thermoplastic feedstock materials for fused deposition modeling (FDM) has been reported by several papers [29,30], mostly related to space and biomedical applications. However, the outgassing properties of PEEK samples produced via FDM have never been tested.…”

Section: Introductionmentioning

confidence: 99%

Additive Manufacturing of Polyether Ether Ketone (PEEK) for Space Applications: A Nanosat Polymeric Structure

et al. 2020

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Recent improvements in additive layer manufacturing (ALM) have provided new designs of geometrically complex structures with lighter materials and low processing costs. The use of additive manufacturing in spacecraft production is opening up many new possibilities in both design and fabrication, allowing for the reduction of the weight of the structure subsystems. In this aim, polymeric ALM structures can become a choice, in terms of lightweight and demisability, as far as good thermomechanical properties. Moreover, provided that fused-deposition modeling (FDM) is used, nanosats and other structures could be easily produced in space. However, the choice of the material is a crucial step of the process, as the final performance of the printed parts is strongly dependent on three pillars: design, material, and printing process. As a high-performance technopolymer, polyether ether ketone (PEEK) has been adopted to fabricate parts via ALM; however, the space compatibility of 3D-printed parts remains not demonstrated. This work aimed to realize a nanosat polymeric structure via FDM, including all the phases of the development process: thermomechanical design, raw material selection, printing process tuning, and manufacturing of a proof of concept of a technological model. The design phase includes the application of topology optimization to maximize mass saving and take full advantage of the ALM capability. 3D-printed parts were characterized via thermomechanical tests, outgassing tests of 3D-printed parts are reported confirming the outstanding performance of polyether ether ketone and its potential as a material for structural space application.

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In Situ Measurement of Carbon Fibre/Polyether Ether Ketone Thermal Expansion in Low Earth Orbit

Cited by 12 publications

References 20 publications

The Thermo-Mechanical Properties of Carbon-Fiber-Reinforced Polymer Composites Exposed to a Low Earth Orbit Environment

The Thermo-Mechanical Properties of Carbon-Fiber-Reinforced Polymer Composites Exposed to a Low Earth Orbit Environment

Effects of electron beam irradiation on hypervelocity impact behavior of carbon fiber reinforced plastic plates

Additive Manufacturing of Polyether Ether Ketone (PEEK) for Space Applications: A Nanosat Polymeric Structure

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