## 4 Conclusions
* Ground stations, especially elements exposed to the elements, require routine maintenance and testing, especially considering that the free space loss on-orbit is much greater than that can be realistically attained without the use of attenuators during end-to-end tests on the ground. Routine tracking and reception of beacon signals from spacecraft already on-orbit will be helpful for functional testing of the ground station and its quality factor. * While expensive, ionizing radiation tests for total ionizing dose and single event effects is still crucial for verifying the robustness of spacecraft avionics and validating the ability of the spacecraft to recover from single event effects. Power cycling recovery mechanisms need to be present for individual electrical circuits in the EPS, in addition to for other subsystems. * Documentation and discussion of lessons learned during the development process and operational period are just as valuable as design reviews, ensuring that the experiences gained are passed on and applied to the development and improvement of future spacecraft systems and missions. IDEASSat demonstrated success in surviving launch and verifying ADCS, autonomous operation, and duplex communication capabilities. The spacecraft also showed healthy thermal, power, and structural margins, validating the design and workmanship abilities of the student team. The spacecraft was found to be sensitive to single event latch-ups in the EPS reset circuit design, which is an important lesson learned for future spacecraft. Corrections have been applied to the EPS design to ensure that this fault is not present on future spacecraft developed at NCU. Persistence of flight software variables damaged by SEU following power cycling also indicate the need for careful consideration in the use of regular variable logging to non-volatile memory, as well as the need for more regular application of error correction and detection methods in such cases. The positive and negative lessons learned from IDEASSat will be implemented in the continued development of NCU spacecraft, to ensure that future spacecraft learn from the experiences of this first mission. [PERSON] served as system engineer for the IDEASSat team and wrote the initial draft of this manuscript; [PERSON] served as project manager for IDEASSat, acquired funding, and revised this manuscript; [PERSON] was payload PI and developer of CIP; [PERSON]-Y.T., K.-L.C., H.-T.L., R.T.-L., C.-T.L., W.-H.L., [PERSON], [PERSON], [PERSON], [PERSON], [PERSON], [PERSON] and [PERSON] were members of the IDEASSat development, integration, and operations team; [PERSON] assisted with science mission definition and funding acquisition; [PERSON], [PERSON], [PERSON], [PERSON] and [PERSON] assisted with reception of IDEASSat beacon packets using ground stations at their respective institutions. All authors have read and agreed to the published version of the manuscript. Fabrication and integration of the IDEASSat spacecraft was covered under contract NSPO-S-106035 from the Taiwan National Space Organization (NSPO) to National Central University. The cost of launch was covered by NSPO and contracted to Heliox Cosmos and ISILAUNCH. Development of the spacecraft engineering model, personnel, ground equipment, and flight operations costs at NCU were supported by Taiwan Ministry of Science and Technology (MOST) grants 105-2111- M-008-001-MY3, 107-2111-M-008-002-MY3, 108-2636-M-008-002, 109-2636-M-008-004, 110-2636-M-008-002, and 111-2636-M-008-004, as well as the Higher Education SPROUT grant to the Center for Astronautical Physics and Engineering from the Taiwan Ministry of Education. The testing and flight data presented in this study are available on request from the corresponding author. The data are not publicly available due to non-disclosure agreements signed with COTS hardware providers, as well as the nature of said data being for internal development use.