TID is generally classified into large-scale TID (LSTID) and medium-scale TID (MSTID) (Hernández et al., 2011). The LSTIDs have a period of >1 hr, move faster than 400 m/s, and have a horizontal wavelength of >1,000 km (Hunsucker, 1982). The main driver of LSTID is believed to be Joule heating, which results from

Plasma technologies play an essential role in our contemporary life, such as in food pasteurization, the disinfection of medical tools, and the manufacture of semiconductors. Accordingly, plasma diagnoses using various methods (e.g., Abdu et al., 1991;Lee et al., 2013;Takahashi et al., 1981) are becoming more and more important. Langmuir Probe (LP) was first designed by Langmuir in 1924 to diagnose gas discharge in laboratory chambers (Langmuir & Mott-Smith, 1924) and has been intensively used for observing ionosphere and magnetosphere in space (Marks, 2011). It applies a variable voltage (V) to a conducting probe surface, after which the electric current (I) collected by the probe is measured (Hoang et al., 2019;Marholm & Marchand, 2020;Oyama, 2015;Smirnov et al., 2021). The current-voltage (I-V) characteristics curve, which represents the relationship between the applied voltage, also called "bias," and the measured current (Amatucci et al., 2001), is a key output from the probe. It should be noted that the spacecraft is subject to the sheath effect, which alters the properties of the plasma within the Debye length. Therefore, the mounting posts of LPs should provide enough spatial separation

In this paper, the contents of the design and development process of the 6U micro-satellite Snipe (SNIPE, national name Toyosat; small scale magnetospheric and Ionospheric plasma experiment ), which was developed to observe the near-global space environment through polarization flight for the first time in Korea, were described. Snipe performs transversal flight to observe the Earth's surrounding space environment in three dimensions, and aims to simultaneously observe the space plasma density and temperature in the ionosphere, as well as temporal changes in the solar magnetic field and electromagnetic waves. In this way, it was developed by dividing it into a test certification model (EQM) and a flight model (FM) to perform the actual mission for at least six months, away from developing a cube satellite for shortterm space technology verification or manpower training. Currently, Snipe, which has completed the development of a total of four FM and completed all space environment tests, is scheduled to launch 2023.

The Small Scale magNetospheric and Ionospheric Plasma Experiment (SNIPE)'s scientific goal is to observe spatial and temporal variations of the micro-scale plasma structures on the topside ionosphere. The four 6U CubeSats (~10 kg) will be launched into a polar orbit at ~500 km. The distances of each satellite will be controlled from 10 km to more than ~1,000 km by the formation flying algorithm. The SNIPE mission is equipped with identical scientific instruments, Solid-State Telescopes(SST), Magnetometers(Mag), and Langmuir Probes(LP). All the payloads have a high temporal resolution (sampling rates of about 10 Hz).Iridium communication modules provide an opportunity to upload emergency commands to change operational modes when geomagnetic storms occur. SNIPE's observations of the dimensions, occurrence 연구논문

The small-scale magnetospheric and ionospheric plasma experiment (SNIPE) is a mission initiated by the Korea Astronomy and Space Science Institute (KASI) in 2017 and comprises four 6U-sized nano-satellites (Korea Astronomy and Space Science Institute Satellite-1, KASISat-1) flying in formations. The main goal of the SNIPE mission is to investigate the space environment in low Earth orbit at 500-km. Because Iridium & GPS Board (IGB) is installed on the KASISat-1, a communication simulation is required to analyze the contact number and the duration. In this study, communication simulations between the Iridium satellite network and KASISat-1 are performed using STK Pro (System Tool Kit Pro Ver 11.2) from the AGI (Analytical Graphics, Inc.). The contact number and durations were analyzed by each orbit and date. The analysis shows that the average access number per day is 38.714 times, with an average of 2.533 times per orbit for a week. Furthermore, on average, the Iridium satellite communication is linked for 70.597 min daily. Moreover, 4.625 min is the average duration of an individual orbit.