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Finally, the current level of the experimental work is presented, which is prior to investigation of the impact modification on the electrostatic lofting of the silica dust grains in the vacuum chamber. In addition, electrostatic forces are compared to the gravity force and the contact forces for the micron and submicron sized dust particles, and it has been seen that the repulsive force between the charged dust grains can be stronger than the other forces. In this study, we investigate different ambient plasma conditions to understand how the lunar dust particles are mobilized under the variation of surface potential, dust potential, electric field and the plasma sheath above the lunar terminator. Therefore, electrostatic forces acting on the dust grains can be described as the repulsive Coulomb force between charged grains and the force resulting from the surface electric field due to the plasma sheath above the surface. Recent studies have shown that dust grains can be transported in the laboratory experiments due to charging within micro-cavities between the particles. In conclusion, it will be possible to estimate the dust population in a two-dimensional plane near the terminator region relative to the camera field of view under various solar wind conditions, solar flares and CMEs.

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Last, the camera code uses this information in order to determine the dust heights in the camera perspective, which is dependent on the camera lens parameters as well.

OMNIWEB FOR OMNI HOTELS SIMULATOR

Third, the satellite flight simulator code determines the position, attitude and the time of passage above the terminator region of the CubeSat as well as the position of the Moon with respect to the Earth and the Sun. Therefore, dependence of the dust lofting on different parameters such as electron temperature, solar wind bulk velocity or plasma density can be explained from the results. Second, lunar dust transportation code calculates the maximum heights that the dust grains can reach under those conditions for the particles in micron to submicron range. First, lunar surface charging code uses solar wind data such as the density of plasma, solar irradiance, the thermal energies of protons and electrons and solar wind bulk velocity, and it calculates the lunar surface potential, electric field and Debye length from the subsolar point to the terminator region by the probe equations.

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The simulation software contains several modules, which are developed on Matlab and Simulink. For this reason, a simulation environment is being developed in order to figure out which space environment conditions are most suitable to observe the LHG. Aoba VELOX-IV (AV4), which is a 2U CubeSat developed by Nanyang Technological University and Kyushu Institute of Technology, will serve as a platform for technology validation towards a future lunar mission to observe the LHG however, it is required to understand how this physical mechanism fundamentally occurs in order to be able to observe it. Therefore, they can transport the lunar dust by electrostatic forces on the lunar surface, and it has been suspected to be the reason of lunar horizon glow (LHG) above the lunar terminator over the years. In addition, the variability of the solar wind as well as release of coronal mass ejections (CMEs) charges the lunar surface to various potential levels. Moreover, the Moon’s ambient plasma conditions vary through its orbit by passing through the magnetotail and the solar wind. The lunar surface is electrically charged directly by interaction with a wide variety of plasma environments and the emission of UV and X-rays from the Sun since the Moon has neither a global magnetic field nor a dense atmosphere.

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