De-Orbit Maneuver Demonstration Results of Micro-Satellite ALE-1 with a Separable Drag Sail
Source abstract
Abstract
ALE-1, a micro-satellite created for the demonstration of artificial shooting stars, required orbital descent before mission execution due to safety aspects in orbit. ALE-1 utilized a drag sail called SDOM (Separable De-Orbit Mechanism) for a passive de-orbit maneuver, which was successfully completed, lowering the orbit from about 500 km down to about 400 km. This paper summarizes the detailed history of satellite operation and the results of the de-orbit maneuver demonstration during the past three years. Although the SDOM sail faced difficulty in keeping the desired deployed shape of the drag sail due to mechanical troubles, by letting the sail be a drag flag instead, it could still deliver a meaningful de-orbit performance to allow the satellite to successfully lower the orbit as planned. The de-orbit effect of the drag flag was evaluated using comparisons between orbit propagation simulations and the actual orbit transition flight data provided in the form of TLE (Two-Line Element) sets. Through this study, it is demonstrated that the SDOM can provide orbit transfer capabilities for satellites. Furthermore, the de-orbit performance of the drag flag can be evaluated, which could be an important reference for the future implementation of de-orbit devices to solve space debris problems.
Source: crossref · Quality: baseline
Research context
OpenAlex topics: Ionosphere and magnetosphere dynamics · Astro and Planetary Science · Space Satellite Systems and Control
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
Affiliations
Department of Aerospace Engineering, Tohoku University, Sendai 980-8579, Japan
ALE Co., Ltd., Tokyo 105-0012, Japan
Nakashimada Engineering Works, Ltd., Hirokawa 834-0196, Japan
References (28)
Show source-provided references
1. (2023, February 01). Innovative Satellite Technology Demonstration Program. Available online: http://www.kenkai.jaxa.jp/eng/research/innovative/innovative.html.
2. First Launch in Months: Japan’s Epsilon Launcher and Its Evolution
3. Qualification results of a sail deployment mechanism for active prevention and reduction of space debries
4. A series of de-orbit mechanism for active prevention and reduction of space debris
5. Pala, A., Kuwahara, T., Takeda, K., Shibuya, Y., Sato, Y., Fujita, S., Suzuki, D., and Kaneko, T. (2022, January 9–12). Orbital Maneuver Evaluation of Micro-satellite ALE-1 with a Separable Drag Sail. Proceedings of the 2022 IEEE/SICE International Symposium on System Integration (SII), Narvik, Norway.10.1109/SII52469.2022.9708783 ↗
6. Double Fail-Safe Attitude Control System for Artificial Meteor Microsatellite ALE-1
7. Structural Design and Verification of Aeronomy Study Satellite ALE-1
8. Konaka, M., Fujita, S., Sato, Y., Shibuya, T., Kuwahara, T., and Kamachi, K. (2018, January 1–5). Evaluation of thermal analysis of orbital environment of microsatellite ALE-1. Proceedings of the 69th International Astronautical Congress: Involving Everyone, IAC 2018, Bremen, Germany.
9. Thermal Design and Evaluation of the Microsatellite ALE-1
10. Shibuya, Y., Kuwahara, T., Sato, Y., Fujita, S., Watanabe, H., and Mitsuhashi, Y. (2021, January 25–29). Orbit Design and Analysis of Artificial Meteors Generating Micro-satellites. Proceedings of the International Astronautical Congress, IAC 2021, Dubai, United Arab Emirates.
11. Shibuya, Y., Sato, Y., Tomio, H., Kuwahara, T., Fujita, S., Kamachi, K., and Watanabe, H. (2021, January 11–14). Development and Demonstration of the Mission Control System for Artificial Meteor Generating Micro-satellites. Proceedings of the 2021 IEEE/SICE International Symposium on System Integration (SII), Iwaki, Japan.10.1109/IEEECONF49454.2021.9382604 ↗
12. High Precision Orbit Determination Method Based on GPS Flight Data for ALE-1
13. Orbit Verification Results of the De-Orbit Mechanism Demonstration CubeSat FREEDOM
14. Tomioka, Y., Yoshida, K., Sakamoto, Y., Kuwahara, T., Fukuda, K., and Sugimura, N. (2012, January 16–18). Lessons learned on structural design of 50 kg micro-satellites based on three real-life micro-satellite projects. Proceedings of the 2012 IEEE/SICE International Symposium on System Integration (SII), Fukuoka, Japan.10.1109/SII.2012.6427314 ↗
15. A sail deployment mechanism for active prevention and reduction of space debries
16. A Japanese microsatellite bus system for international scientific missions
17. Structural Design of De-orbit Mechanism Demonstration CubeSat FREEDOM
18. System Design, Development and Ground Verification of a Separable De-Orbit Mechanism for the Orbital Manoeuvre of Micro-Satellite ALE-1
19. Space Demonstration of Boom Extension and De-orbit Sail Deployment of the Separable De-orbit Mechanism of Micro-satellite ALE-1
20. Time-of-Flight Monitoring Camera System of the De-orbiting Drag Sail for Microsatellite ALE-1
21. Kuwahara, T., Pala, A., Potier, A., Shibuya, Y., Sato, Y., Fujita, S., Suzuki, D., and Kaneko, T. (2022, January 9–12). Orbital Demonstration of Gossamer Structure Shape Estimation using Time-of-Flight Camera System. Proceedings of the 2022 IEEE/SICE International Symposium on System Integration (SII), Narvik, Norway.10.1109/SII52469.2022.9708770 ↗
22. Vallado, D.A., and McClain, W.D. (2013). Fundamentals of Astrodynamics and Applications, Microcosm Press. [4th ed.].
23. Montenbruck, O., and Gill, E. (2005). Satellite Orbits, Springer.
24. Establish the environment to support cost-effective and rapid development of micro-satellites
25. Low-Cost Simulation and Verification Environment for Micro-Satellites
26. NRLMSISE-00 empirical model of the atmosphere: Statistical comparisons and scientific issues10.1029/2002JA009430 ↗
27. (2023, February 01). National Geospatial-Intelligence Agency Office of Geomatics. Available online: https://earth-info.nga.mil/.
28. Fujita, K., and Noda, A. (2009, January 22–25). Rarefied Aerodynamics of a Super Low Altitude Test Satellite. Proceedings of the 41st AIAA Thermophysics Conference, San Antonio, TX, USA.10.2514/6.2009-3606 ↗