Polymerisation of composite materials in space environment for development of a Moon base

Kondyurina, Irina; Kondyurin, Alexey; Lauke, Bernd; Figiel, Łukasz; Vogel, Roland; Reuter, Uta

doi:10.1016/j.asr.2005.05.031

Cited by 31 publications

(6 citation statements)

References 4 publications

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“…Experimental data on degradation of epoxy resin composites during SETAS, LDEF, MEEP, SARE, AORP, DSPSE, ESEM, EuReCa, HST, MDIM, MIS and MPID missions in LEO [15] are available. However, because detailed investigation of the kinetics of reactions in the composites in space is expensive and difficult, a number of investigations were done in laboratory free space environment simulators, where individual factors or combinations of factors prevalent in free space are simulated [16][17][18].…”

Section: Introductionmentioning

confidence: 99%

Etching and structure transformations in uncured epoxy resin under rf-plasma and plasma immersion ion implantation

Kondyurin

Bilek

2010

Nuclear Instruments and Methods in Physics Research Section B:

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Section: Introductionmentioning

confidence: 99%

Etching and structure transformations in uncured epoxy resin under rf-plasma and plasma immersion ion implantation

Kondyurin

Bilek

2010

Nuclear Instruments and Methods in Physics Research Section B:

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“…These high‐temperature variations may cause accelerated thermal aging of polymers, molecular destruction, de‐polymerization, and cross‐linking. As a result the durability of polymer materials in the space environment is reduced and can lead to their fracture [24]. This indicates clearly the fact that we may not casually neglect the conductive heat transfer in solid or not so thin‐walled cylindrical spacecrafts.…”

Section: Introductionmentioning

confidence: 99%

Computational modeling and analysis of thermal characteristics of a rotating spacecraft subjected to solar radiation

Gadalla

Wahba

2011

Heat Trans. Asian Res.

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This paper presents a computational modeling for the temperature distribution of a rotating thick-walled cylindrical spacecraft subjected to solar radiation. The inner surface of the spacecraft is thermally insulated while the outer surface is subjected to concurrent events of solar incidence and radiative heat dissipation to space. The governing equation for the normalized temperature is discretized using a finite difference scheme and Successive Line Over-Relaxation (SLOR) is used to solve the resulting system of algebraic equations. Numerical simulations of temperature distribution on the spacecraft for different spinning speeds, angular positions, and different radii are discussed and evaluated for both linearized and nonlinear boundary conditions. Comparative analysis between the computational modeling and the exact analytical solution for the linearized boundary condition is presented. The results indicate that the outer surface temperature distribution of the spacecraft is nearly independent of the angular position; at sub-cylindrical surface, this independence is achieved at low angular velocity. Moreover, numerical simulations show that the use of the linearized boundary condition at the outer surface presents a good approximation for the case of high-speed spinning spacecrafts, while it results in significant errors in the temperature field in the case of stationary and low-speed spinning spacecrafts.

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“…Polymer degradation after exposure in real and simulated free space environment has been observed by optical, electron and atomic force microscopes as an increase in surface roughness; by XPS and FTIR spectroscopy as oxidation of surface layer; by mechanical and thermo-mechanical methods as a decrease in the strength and an increase in the Young's modulus and the glass transition temperature [22][23][24][25][26][27][28][29][30]. There does not appear to be, however, any detailed investigation of the effects of stratospheric conditions on polymer materials.…”

Section: Introductionmentioning

confidence: 99%

Radiation damage of polyethylene exposed in the stratosphere at an altitude of 40 km

Kondyurin

Kondyurina

Bilek

2013

Polymer Degradation and Stability

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Low Density Polyethylene (LDPE) films were exposed at an altitude of 40 km over a 3 day NASA stratospheric balloon mission from Alice Springs, Australia. The radiation damage, oxidation and nitration in the LDPE films exposed in stratosphere were measured using ESR, FTIR and XPS spectroscopy. The results were compared with those from samples stored on the ground and exposed in a laboratory plasma. The types of free radicals, unsaturated hydrocarbon groups, oxygen-containing and nitrogen-containing groups in LDPE film exposed in the stratosphere and at the Earth's surface are different. The radiation damage in films exposed in the stratosphere are observed in the entire film due to the penetration of high energy cosmic rays through their thickness, while the radiation damage in films exposed on the ground is caused by sunlight penetrating into only a thin surface layer. A similarly thin layer of the film is damaged by exposure to plasma due to the low energy of the plasma particles. The intensity of oxidation and nitration of LDPE films reflects the difference of atmospheric pressure on the ground and in the stratosphere. The highdensity radiation damage of the LDPE films above the ozone layer in the stratosphere is caused by primary cosmic rays as well as collision induced cosmic ray air showers, and is consistent with the measured flux of cosmic radiation. The results show, that stratospheric flights can be used to simulate the effects of space environments during interplanet space flights for the purposes of investigating the degradation of polymer materials.

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Polymerisation of composite materials in space environment for development of a Moon base

Cited by 31 publications

References 4 publications

Etching and structure transformations in uncured epoxy resin under rf-plasma and plasma immersion ion implantation

Etching and structure transformations in uncured epoxy resin under rf-plasma and plasma immersion ion implantation

Computational modeling and analysis of thermal characteristics of a rotating spacecraft subjected to solar radiation

Radiation damage of polyethylene exposed in the stratosphere at an altitude of 40 km

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