Development of Nano-Satellite OrigamiSat-1 with Highly Functional Deployable Membrane By Hiroki NAKANISHI1),Hiraku SAKAMOTO1), Hiroshi FURUYA1), Masahiko YAMAZAKI2), Yasuyuki MIYAZAKI2), Akihito WATANABE3), Kazuki WATANABE4), Ayako TORISAKA-KAYABA5), and Mitsushige ODA1) 1)Tokyo Institute of Technology, Tokyo, Japan 2)Nihon University, Chiba, Japan 3)Sakase Adtech, Co., Ltd., Fukui, Japan 4)WEL Research Co., Ltd., Chiba, Japan 5)Tokyo Metropolitan University This paper discusses a design of a 3U CubeSat, which will demonstrate an advanced membrane space structure in orbit. The objective of the CubeSat development is the establishment of research/development hub which enables the realization of innovative space deployable structures. The 3U CubeSat is designed as a pilot project to achieve the objective. This paper describes the CubeSat missions derived from the bigger development objective, and explains the system design of the CubeSat. Key Words: Gossamer Structures, Small Satellites, Nano Satellites, CFRP Boom 1. Introduction be launched in FY2018 using Epsilon rocket. Advanced lightweight space structures, especially membrane 2. Objective of CubeSat Development structures, have been widely studied for enabling future space applications. Applications that will benefit from such structures In order to establish a research and development hub for includes deorbiting system, solar array, reflectors, sun shield, space deployable structures, the present authors focus on the phased array antenna, solar sail, aerobrake/aerocapture system, following three key activities. and occulter. However, it is difficult to predict deployment dynamics and deployed shapes of space membrane structures (F1) Development of space demonstration scheme for ad- through ground tests. This is because the effects of gravity and vanced space deployable structures atmosphere have significant impact on the behavior of mem- (F2) Development of design and verification methodologies brane structures on the ground. For this reason, numerical struc- for space deployable structures through the synthesis of tural analyses were intensively used during the development of experiments and numerical analyses the world-first solar sail demonstrator IKAROS. 1) But the ex- (F3) Establishment of a community for research and develop- periments to evaluate the accuracy of the numerical analyses ment of space deployable structures where knowledge re- ff are also difficult to conduct, because even the scale models for tention is possible over di erent generations membrane space structures are significantly influenced by grav- These activities for establishing research/development hub is ity and atmosphere. now called ORIGAMI (ORganizatIon of research Group on Ad- A possible approach to overcome the aforementioned prob- vanced deployable Membrane structures for Innovative space lem is the use of CubeSats. Recently various CubeSat compo- science) project. And as the first pilot space demonstration nents are available as commercial products; thus, the effort re- satellite, the development of a 3U CubeSat, OrigamiSat-1, has quired for CubeSat development has been significantly reduced. been started. The objective of OrigamiSat-1 is to accomplish In addition, Japan Aerospace Exploration Agency (JAXA) of- the following three missions. fers launching opportunities for small satellites using Epsilon rockets and using International Space Station. It is significantly (M1) Membrane deployment mission: To contribute to the useful to obtain a capability to conduct experiments of space realization of future applications, an highly functional deployable structures in space using CubeSats, and to establish membrane structure is deployed, and its deployment be- a community that supports such research and development ac- havior and deployed shapes are measured in orbit. tivities. (M2) Space-demonstration scheme development mission: To To this end, the present authors have started the establishment obtain space-demonstration scheme for researchers of of a research/development hub for space deployable structures space deployable structures, commercially available through developing an actual 3U CubeSat as a pilot project. components are used or developed. In this paper, the CubeSat design, which aims at contribut- (M3) Amateur radio mission: To enhance radio communi- ing to the establishment of research/development hub, is dis- cation skills, 5.84GHz high-speed transmission from cussed. Section 2 defines the CubeSat’s missions, and Section space 2) is used. 3 describes the system design to implement the missions. This CubeSat, named OrigamiSat-1, has been selected by JAXA to V]CQ7:GCV IVIG`:JV .1J `1CI QC:` HVCC L .1J :J VJJ: %GV: % V]CQ7:GCV I: :IV`: Fig. 1. 3U CubeSat, OrigamiSat-1. The deployable camera system, illustrated in Fig. 2, takes pictures of the deployed membrane on orbit. It has approxi- mately 1m-length deployable mast, and the camera is installed on the tip of the deployable mast. Finally, Fig 5 shows the mission sequence. (1) the CubeSat is released from a rocket, (2) the deployable antennas are de- ployed, (3) the extensible mast is extended, and finally (4) the %%J1 6 VJR:GCV VIG`:JV H:IV`:%J1 RV]CQ7IVJ %J1 highly functional membrane is deployed. Fig. 2. Components of OrigamiSat-1. 4. Summary Table 1. Specifications of OrigamiSat-1. Size Approx. 100×100×340 mm The missions of the 3U CubeSat OrigamiSat-1 are selected Mass Approx. 4.0 kg in order to contribute to the establishment of research and de- Launch By Epsilon rocket in FY2018 velopment hub for advanced space deployable structures. The system design of OrigamiSat-1 is described. 3. CubeSat Design Acknowledgments In order to accomplish the three missions, a preliminary de- The work described in this paper has been supported by Min- sign of OrigamiSat-1 has been considered. Figure 1 shows an istry of Education, Culture, Sports, Science and Technology in on-orbit image of OrigamiSat-1. Table 1 shows basic specifica- Japan. In addition, the development of OrigamiSat-1 is sup- tions of the CubeSat. ported by the solar sail working group in ISAS/JAXA. The au- Figure 2 shows the on-board components and Fig. 3 shows thors appreciate the support. the system diagram of OrigamiSat-1. The system consists of four major subsystems: (i) bus, (ii) membrane deployment sys- References tem, (iii) extendable camera system, and (iv) ground station. For the bus, most components are composed of commercial off- 1) Shirasawa, Y., Mori, O., Miyazaki, Y., Sakamoto, H., Hasome, M., the-shelf (COTS) components. This design aims at facilitating Okuizumi, N., Sawada, H., Furuya, H., Matsunaga, S., and Natori, the future space demonstration of advanced space deployable M. C., “Analysis of Membrane Dynamics Using Multi-Particle Model structures by university/company researchers. for Solar Sail Demonstrator “IKAROS”,” AIAA Paper 2011-1890, 2011. The membrane deployment system deploys a membrane- 2) Tanaka, T., Kawamura, Y., and Tanaka, T., “Development and op- 3) boom integrated structure, proposed by the present authors. erations of nano-satellite FITSAT-1 (NIWAKA),” Acta Astronautica, Its membrane folding pattern, called rotationally skew fold- Vol. 107, 2015, pp. 112–129. ing, 4) enables the attachment of thin-film devices on the mem- 3) Furuya, H., Satou, Y., Sakamoto, H., Takai, M., Okuizumi, N., Natori, brane, such as thin-film solar cells and thin SMA antennas. The M. C., Torisaka, A., Yokomatsu, T., Kurashige, H., and Watanabe, A., “Deployment Experiments of Wrapping Fold Boom-Membrane Inte- prototype of the membrane deployment system of OrigamiSat-1 grated Space Structures for De-Orbiting Satellites,” 30th International is shown in Fig. 4. The deployment experiment on the ground is Symposium on Space Technology and Science, No. 2015-c-45, Kobe, shown in Fig. 6. In this experiment, the thin devices are not at- Hyogo, Japan, July 2015. tached on the membrane yet. The tips of the deployable booms 4) Furuya, H., Inoue, Y., and Masuoka, T., “Deployment Characteristics are suspended from the ceiling for gravity compensation. of Rotationally Skew Fold Membrane for Spinning Solar Sail,” AIAA % `Q%JR : 1QJ : V`7 QC:`:JVC& ^C7RV]:HV%GV: :JR:CQJV: V`7_ Q:`&V&%J 6 VJR:GCV H:IV`: &VJ&Q`& 2$ 6 VJR:GCVI:& V`VQH:IV`:& %J.1G1 H1`H%1 & 1RVR01V1H:IV`:& QJ `QCJ1 ^2:&]GV``71_ ^C7RV]:HV_ Q01VH:IV`: 8%JH.CQH@ 8& IVH.:J1&I ^QI]:HV :JQ1JR _ $% VIG`:JV RV]CQ7IVJ )6L26 HQJ `QCCV` VIG`:JVRV]CQ7IVJ IVH.:J1&I 07& V`V&1& 8 0< ).1JR`1CI&QC:`HVCC& R:I]V` $)6 26 )6 IQR%CV QJ `QCJ1 ^ 1&.1I%&VJ_ ^ 1&.1I%&VJ_ :J VJJ: ^%_ R I:$JV 8 < 6 :J VJJ: 6 :J VJJ: )VI]V`: %`VHVJ&Q` :J VJJ: $% Fig. 3. System diagram of OrigamiSat-1. .1JRV01HV VIG`:JV φII5I GQQI IIII `%H %`V Fig. 4. Prototype of highly functional deployable membrane. Paper 2005-2045, 2005. (1) (2) (3) (4) Fig. 5. Mission sequence of OrigamiSat-1. Fig. 6. Deployment test of deployable membrane on ground..