This paper discusses the results of launch environment tests for the engineering qualification model (EQM) of nanosatellite Scale magNetospheric and Ionospheric Plasma Experiment (SNIPE) for scientific missions and lessons learned for the design of nanosatellites. SNIPE is a group of four formation-flying 6U nanosatellites with a range of payloads for missions including space weather measurement. We developed the EQM to verify the preliminary design prior to fabricating the flight model. Launch environment test of EQM was conducted for the first time in 2019, and all failures were corrected and verified at the second 논문 Received: September 15, 2021 Revised: October 12, 2021 Accepted: October 25, 2021 Corresponding author : Min-Ki Kim Tel : +82-42-860-2347 E-mail : mkkim12@kari.re.kr Copyright © 2021 The Korean Space Science Society. This is an Open Access article distributed under the terms of the Creative Commons Attribution Non-Commercial License (http://creativecommons.org/licenses/by-nc/4.0) which permits unrestricted non-commercial use, distribution, and reproduction in any medium, provided the original work is properly cited. ORCID Min-Ki Kim https://orcid.org/0000-0003-1167-6658 Hae-Dong Kim https://orcid.org/0000-0001-9772-0562 Won-Sub Choi https://orcid.org/0000-0002-2369-6210 Jin-Hyung Kim https://orcid.org/0000-0002-3899-0375 KiDuck Kim https://orcid.org/0000-0003-1906-2298 Ji-Seok Kim https://orcid.org/0000-0002-9323-3078 Dong-Hyun Cho https://orcid.org/0000-0001-7113-1102 초소형위성 SNIPE 시제인증모델의 발사환경시험 및 분석 320 | https://doi.org/10.52912/jsta.1.3.319 test conducted in 2021. A notable point of the two tests is that the nanosatellite deployer used in the first test is different from that of the second test. The second deployer has the capability to fix the internal satellite whereas the first deployer just contains and deploys the satellite. Thus actual mechanical loads the satellite receives is reduced for the second test compared to the first test. This work compares the mechanical responses of two tests and proposes general guidelines for structural design of nanosatellites. 핵심어 : 발사환경시험, 도요샛, 초소형위성, 시제인증모델, 초소형위성 발사관, 초소형위성 고정