BIRDS-1 Cubesat Constellation Using Compact UHF Patch Antenna

BIRDS-1 CubeSat Constellation using Compact UHF Patch Antenna

著者 Samsuzzaman Md., Islam Mohammad Tariqul, Kibria Salehin, Cho Mengu journal or IEEE Access publication title volume 6 page range 54282-54294 year 2018-09-19 URL http://hdl.handle.net/10228/00007241 doi: info:doi/10.1109/ACCESS.2018.2871209 Received August 20, 2018, accepted September 12, 2018, date of publication September 19, 2018, date of current version October 17, 2018.

Digital Object Identifier 10.1109/ACCESS.2018.2871209

BIRDS-1 CubeSat Constellation Using Compact UHF Patch Antenna

MD. SAMSUZZAMAN 1, (Member, IEEE), MOHAMMAD TARIQUL ISLAM 1,2, (Senior Member, IEEE), SALEHIN KIBRIA1, AND MENGU CHO2 1Center of Advanced Electronic and Communication Engineering, Universiti Kebangsaan Malaysia, Bangi Selangor 43600, Malaysia 2Laboratory of Spacecraft Environment Interaction Engineering, Kyushu Institute of Technology, Kitakyushu 804-8550, Japan Corresponding authors: Md. Samsuzzaman ([email protected]), Mohammad Tariqul Islam ([email protected]), and Mengu Cho ([email protected]) This work was supported in part by the Kyushu Institute of Technology (Kyutech), Japan, and in part by the LASINE Research Grant and UKM University Research Grants MI-2017-001 and KK-2016-007.

ABSTRACT BIRDS-1 satellites, a constellation of ﬁve identical 1U CubeSats, were designed, manufactured, assembled, integrated, and tested at LASINE Laboratory, Kyutech, Japan. Students from ﬁve nations (Japan, Ghana, Mongolia, Nigeria, and Bangladesh) collaborated to develop a number of CubeSats with coordinated ground coverage, named ‘‘Joint Global Multi-Nation BIRDS,’’ or abbreviated as ‘‘BIRDS.’’ To establish the downlink communication between satellite and Earth, an UHF patch antenna was utilized. Patch antennas offer an ideal solution to Cube satellite communication requirements due to their compact dimension and lightweight. However, the limited surface area available in CubeSats, conventional UHF and VHF patch antennas cannot be used. In this paper, a compact coaxial fed UHF (437.375 MHz) patch antenna system for 1U BIRDS-1 CubeSat (small satellite) is presented. The proposed antenna consists of a spiral meander line patch at the top side and partial ground plane another side of the substrate. A shorting pin has also been utilized to change the resonance to the required UHF band. For the intended 1U BIRDS-1 application, the goal is to mount on satellite body within a limited area of 1U BIRDS-1 satellite. The proposed antenna dimension (0.105λ×0.047λ×0.002λ at 437.375 MHz) and characteristics are compatible with any CubeSat standard structure. A prototype of the antenna was developed with a 1.57-mm-thick single layer Roger’s substrate having a relative permittivity of 2.2, and measured results are consistent with simulation. The proposed UHF antenna has integrated and tested with 1U BIRDS-1 satellite. Finally, the satellite was successfully launched on June 3, 2017, from the John F. Kennedy Space Center, the USA at Low Earth Orbit for earth observations, message relay, space environment, and technology demonstration through the International Space Station.

INDEX TERMS BIRDS, CubeSat, compact planar antenna, a small satellite, UHF.

I. INTRODUCTION there might be an extremely persuasive case for CubeSats to Cube Satellites are tiny cube-shaped small satellites with be used in lots of applications, including technology market- dimension 10 cm per edge and a mass less than 1 kg. ing and sales communications, global observation, and tech- The cubic structure encompasses a specific aluminum box nology demonstration. CubeSats usually use VHF and UHF with solar panels fitted to the exterior walls [1]. Antennas, communication for telemetry and telecommand applications. usually flexible monopoles, are integrated perpendicular to It’s very challenging to design a small antenna for CubeSat the CubeSat faces, in the corners. CubeSats have been mainly communication system because of the CubeSat physical size utilized for university research work giving student’s work- constraint. Usually, impartial versatile monopole antennas ing encounter in developing and screening equipment for are installed using one face of the satellite structure to space [2]. However, it is very clear that the utility worth establish up- and downlink communication. These antennas of CubeSats is usually quickly increasing. Reliable, high- are rolled around the satellite before deployment and kept performance, industrial CubeSats are actually obtainable and setup with monofilament assured utilizing a brief amount

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of Nichrome wire within the spacecraft. Upon deployment, was also exhibited by the TURKSAT CubeSat task. The 25 % a current is passed through the Nichrome wire, which heats wavelength dipole antenna with a width of 3 mm and height and melts the monofilament and warp/unroll the antennas. of 50 cm operates at 145 MHz. Another antenna functions at The use of wire monopoles, though basic, raises serious 435 MHz and includes six-quarter wavelength dipoles like the concerns of deployment failure. For UHF and VHF band receiver antenna [17]. A UHF band (400-450 MHz) antenna communication, large deployable antennas are needed that was used for Communication with a ground station (range) further raise failure potential. Among the primary design for space research using CubeSat [18]. For onboard LAPAN- considerations of Cube satellites is usually an efficient and TUBSAT microsatellite telemetry and telecommand applica- low-cost antenna. Microstrip patch antennas are among the tions, a little UHF music group (428− 468 MHz) antenna main candidates for small satellite communication, especially was manufactured which was monopole-like meander type because of their light-weight, low profile and body mounted linearly polarized and omnidirectional microstrip antenna features [3], [4]. There are many small satellites antennas with dimensions of 160 mm by 140 mm [19]. Besides, are pointed out in various research article such as monopole some UHF antenna band was also presented in the recent antennas, wire antennas, printed inverted-F-shaped anten- various literature for CubeSat or small satellite applications nas (PIFAs), microstrip-patch antennas, helices, and patch [4], [20]–[25]. The antennas offered by above studies are sim- excited cup antennas, were designed for telemetry, tracking, ilar to the designed antenna performance. However, the men- and command in the UHF, VHF band [5]–[7], but all of them tioned dimensions are larger than the allotted space which is are developed for larger than 1U CubeSat dimensions and not compatible in 1U and 2U CubeSatellite. compatible features. In this article, a compact UHF microstrip patch antenna Mathur et al., 2001 explained the look of UHF patch anten- was developed for BIRDS CubeSat application. To achieve nas for the USUsat nano-satellite which is usually a section compact antenna dimension, a meander line patch was of the ION-F constellation. The uplink antenna functioned at designed on one side of the substrate and partial ground 450 MHz, with part length add up to 106.7 mm [8]. In the plane was printed on another side of the substrate. Beside other end of the look spectrum, the task by [9] is an example this shorting pin, technique was also utilized to increase the of how suspended, electrically large areas can show quite electrical length of the antenna. After optimizing the antenna significant bandwidths. Furthermore, resonant-size areas can parameters, a prototype was fabricated and measured in the produce benefits in the number 4-6.5 dBi and bandwidths lab. Then, the proposed antenna integrated and tested with 1U of the few percents [6], [10]–[12]. Alternatively, 3-D struc- BIRDS-1 Satellite in LaSEINE Lab, Kyutech, Japan. Finally, tures comprising folded and stacked radiating areas offer the five 1U BIRDS-1 satellite with UHF patch antenna has average bandwidths and benefits combined, and may also successfully launched in the low earth orbit. become electrically small [13]. C. G. Kakoyiannis et al engi- neered a circularly polarized patch antenna that functions at II. BIRDS-1 SATELLITE 434.8-438 MHz using miniaturization techniques. The Now a day’s small satellites are getting more and more authors focus on the difficulties in developing patch anten- attention due to short incubation time, low cost, and avail- nas at UHF given the scale limitations of CubeSats, ability of highly reliable and efficient COTS (Commercial emphasizing the actual fact that electrically small antenna off-the-shelf) components. Even a small group of university overall performance endures, and recommending the uti- researchers can assemble, test, launch and operate in orbit if lization of patch antennas at higher frequencies such as the launcher is available and if researchers are well trained. 2.4 GHz [14]. The first UoSAT spacecraft utilized VHF Recently, five-nation (Japan, Ghana, Mongolia, Nigeria, and and UHF transmitters with related wavelengths of 2 m and Bangladesh) CubeSat constellation has been designed and 70 cm on constructions typically measuring 58 cm ×35 cm named as ‘‘Joint Global Multi-Nation BIRDS,’’ or ‘‘BIRDS’’. ×35 cm. The body of the spacecraft was shorter than Five identical CubeSats are designed, manufactured, assem- the wavelengths included (SSTL, 2011). Kakoyiannis and bled, integrated, tested, and operated by the researchers Constantinou have designed a UHF band group (436.5 MHz) where each country is responsible for one CubeSat. After the CubeSat Patch Prototype (CSPP) [15]. The rectangular assembling and testing, with the help of Japanese National imprinted CSPP antenna packed with inductive peripheral Space Agency, JAXA, it has sent to ISS (International Space slits with a dimension of 170 mm × 120 mm. Podilchak et al. Station) for deployment to the Low Earth Orbit (LEO). It is designed a concise antenna structure utilizing a four-element operated from ground station of each country and other col- arrayed construction of folded-shorted areas for the proce- laborating countries by amateur radio band. Through this dure at 400 MHz with dimension 150 mm by 150 mm [16]. processes, it can be demonstrated that a 1U CubeSat can be Tiago Freire et. al explained the look and implementation of built and operated successfully in a time frame shorter than the dual-band spring-steel monopole antenna that resonates two years even for countries with limited (or zero) satellite at 438 and 146 MHz, the give food to set up for the antenna, experience with proper design and planning. The mission of and the look of the diplexer for use in a Nano-class satellite the BIRDS- the project is to make the first step toward an known as a 3U CubeSats. The extensive use of UHF and VHF indigenous space program at each country by successfully bands for data and tone of voice marketing communications building and operating the first satellite nation.

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A. BIRDS-1 SATELLITE MISSION The ultimate objective of this project is to build and operate the first satellite of nation that triggers the first step toward indigenous space programs in each country. Students can achieve this by learning the entire processes of a satellite program from mission planning to satellite disposal. It also helps lay down a foundation of the sustainable space program by accumulating human resource in universities. This has also created international networks to assist the growing space programs. In order to accomplish this, BIRDS project has been designed to make a constellation of five identical 1U CubeSat with six missions, such as, Camera (CAM), Digi-singer (SNG), Precise positioning(POS), atmospheric density measurement (ATM), constellation network operation (NET) and single-event-latchup (SEL).

B. BIRDS-1 SATELLITE CONFIGURATION Five CubeSats are designed as 1U (10 cm cube and 1kg) with dimension 100 mm × 100 mm × 113.5 mm CubeSat that is identical (mass, design, payload, communication, ground station, etc.) to each other. Attitude is controlled by a permanent magnet and a hysteresis damper. Five faces are covered by 10 solar cells; each face contains 2 cells in parallel. Six NiMH rechargeable batteries (3S2P) have been decided to provide 5V and 3.3V bus systems. Since Kyutech has the heritage and experience of one small Satellites Horyu-2 [20] operation, most of the BIRDS architecture is based on Horyu-2. To avoid complicacy due to the wire harness, each CubeSat has been planned to follow so-called backplane style, where different subsystems module such as OBC, EPS, COM, ADCS, Cam, transceivers, was placed on a backbone like a rail, according to the design of UWE- 3 of University Wurtzburg, Germany [21]. The solar panel was placed on ﬁve faces and one face is assigned to the antenna. For the UHF patch antenna, the dedicated area was 80 mm × 45 mm. Figure 1 was depicted the 1U BIRDS-1 satellite (a) structural conﬁguration (b) Communication step c) Communication block diagram. From the Fig. 1(c) communication block, it was planned to use VHF 1200bps uplink and UHF (437.372-437.375 MHz) 1200/9600bps data downlink. Two Cameras and a patch antenna for the mission are mounted on the +Y face. Solar panels are mounted on other faces of the CubeSat. The access port and RBF pins are on the −Y face. The deployable antenna has deployed from both + Z and −Z axis. Separation springs for interfacing with the Japan Experimental Module Small Satellite Orbital Deployer (J-SSOD) are mounted diagonally on the rail standoffs on the − Z face of the CubeSat. Deployment Switches are mounted adjacent to the two separation springs. Preceding satellite HORYU -II, launched in the middle of the calendar year 2012, operates in the low UHF band. Nevertheless, the deployable character of UHF antenna combined with the non- rigid framework eventually resulted in failure of the UHF conversation after almost twelve months in LEO. Therefore FIGURE 1. 1U BIRDS-1 satellite (a) structural configuration imprinted UHF antenna with the physical restrictions and (b) communication step (c) communication block diagram.

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requirements, deﬁned by the objective protocol and evaluation of the prior HORYU-II, HORYU-IV and BIRDS objective mission data are summarized in Table 1 [4], [22].

TABLE 1. BIRDS UHF band antenna requirements.

III. ANTENNA GEOMETRIC LAYOUT DESIGN The antenna design was started with a survey of state of the art patch antenna technology for CubeSat’s satellites and various miniaturization techniques. Several recent references were FIGURE 2. Schematic layout of the proposed overall design of the UHF also studied from the books, journal proceeding, research arti- antenna. cles. The design involves a different combination of miniaturization techniques of patch antennas like folded meander line [23], [24], partial ground plane [25], and shorting pin [26] in the form of a rectangular patch, is then placed in the for small satellite applications. Commercial electromagnetic middle of the spiral section. An inverted L shaped antenna software based on finite element method (FEM) and Method configuration is achieved using a shunt inductance which is of Momentum (MoM) was used to obtain the optimized used to allow matching of the antenna impedance through design parameters. A parameter such as reflection coefficient, shorting pin to 50 ohms without the need for discrete coor- radiation pattern and efficiency has been studied. Rogers’s dinating components. Finally, a small triangular capacitive substrate has been considered as a substrate material of the stub is printed on the ground plane in order to allow a degree proposed antenna design because its high-reliability char- of fine-tuning of the antenna’s resonant frequency. The pro- acteristic’s for aerospace applications [27]. For restrictions posed antenna is mechanically robust, compact in profile, of 1U BIRDS-1 cube satellite space, 50-ohm MMCX (Micro- lightweight, and good thermal properties and thus suitable Miniature Coaxial) coaxial probe feed line has been utilized for space applications. Due to the use of an MMCX coaxial for design requirements. The patch was connected through fed line and the narrow width of the meander patch, the pro- a drilled hole in the substrate and ground plane and feed line posed antenna can easily fit within narrow space within the was adjusted for MMCX connector. To design a λ0/4 resonant communication device. Final optimized design parameter of patch antenna at 437.375 MHz would require dimensions of the realized antenna geometric layout is presented in Table 2. ∼172 mm excluding a ground plane which is totally unsuit- From simulated surface current distribution magnitude at able for 1U BIRDS-1 satellite. This size constraint means that 437.375 MHz which is shown in Figure 3, large current flows a λ0/4 antenna can be an impractical and significantly reduced in the spiral and inductive section with a smaller current flow amount of antenna sizes is, therefore, necessary. However, on the capacitive stub. The analysis unveils that resonant reducing the size can negatively impact the efficiency, gain, frequency is mainly determined by the full total electrical and bandwidth of the antenna [28]. Figure 2 depicts the amount of the feed line with the spiral section as well as the schematic layout of the proposed design of the UHF antenna. perimeter amount of the capacitive loading patch section. The patch antenna structure is based on spiral and folding techniques and the partial ground plane that covered UHF IV. ANTENNA PERFORMANCE ANALYSIS band. The radiating antenna length is calculated about λ/4 A prototype of the proposed antenna was fabricated and (λ is the wavelength) and is optimized to 437.375 MHz. measured, as illustrated in Figure 4. Experimental results are To decrease the resonant length, the radiating element is measured using Agilent N5227A PNA microwave network first folded using a turn square-spiral section with feed line. analyzer. Figure 5 displays the return-loss magnitude while To further decrease the electrical size, a capacitive loading, a function of the frequency for the designed UHF patch

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TABLE 2. Optimized dimension of the proposed antenna.

FIGURE 5. The simulated and measured reflection coefficient of the UHF antenna.

FIGURE 3. Surface current distribution of the proposed UHF antenna. FIGURE 6. 2D measured radiation pattern of the antenna.

FIGURE 4. UHF antenna prototype (a) Top view (b) Bottom view. antenna system. Speciﬁcally, the ﬁgure displays the outcomes obtained by way of EM numerical simulations, computed with CST, and by measurements, performed by utilizing a PNA microwave network. Both simulations (dashed line) FIGURE 7. Flight model of the 1U BIRDS-1 satellite. and experimental (straight line) outcomes highlight that the antenna is usually well matched at the required operating range from 437.372-437.375 MHz. Moreover, the measured frequency satisfying the necessity on the S11 is well below frequency behavior is in a very good agreement with the the value of −10 dB at 448 MHz-418 MHz(Relative Band- simulation results. The radiation characteristics of the pro- width 6.92%) which cover the desired operating frequency posed UHF antenna with satellite structure was measured

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TABLE 3. Summary of the proposed BIRDS UHF antenna. A. BIRDS-1 CubeSat LINK BUDGET ANALYSIS When arranging CubeSat missions, an essential fact is the power budget expected simply by the radio communication subsystem, which allows a CubeSat to switch information with ground stations and/or additional CubeSats in the orbit. The power budget a CubeSat can devote to the communication subsystem is bound by the stringent restrictions on the full total power available, due to its compact dimension and light-weight that limit the sizes of the CubeSat power components like batteries and solar power panels [35]. Amongst the various electronic modules of a CubeSat, the radio communication system is an essential one, since it allows the CubeSat to switch information and connect to ground stations and also with other CubeSats. Therefore the designing the communication system of a CubeSat entails a link budget evaluation to determine power requirements, select appropriate equipment, in Satimo near-ﬁeld measurement systems. The measured and set up modulation parameters for signal transmission normalized radiation pattern at the resonant frequency is and reception. The purpose of radio link design is to make presented in Figure 6. The total efﬁciency of the proposed sure that a trusted communication link could be established UHF antenna at the resonance frequency is approximately between a radio transmitter and its own associated receiver if 56% with 0.55 dB of realized gain and 1.01 dB peak gain. adequate power is offered by the radio receiver to close the The measured radiation pattern in both azimuth and elevation link that is to meet up a required signal to noise ratio (SNR) planes 437.375 MHz is illustrated in Figure 6, where it can value. We’ve summarized the downlink frequency link budget be observed that the antenna shows nearly omnidirectional in Table 5 by available link budget equation to judge digital radiation pattern at azimuth plane. A summary of the antenna data radio link [36]: is presented in Table 3. The performance of the proposed Eb SNRdB = 10 log10( ) antenna has been compared with existing UHF antennas, N0 tabulated in Table 4. Considering the comparison criteria in Pt Gt Gr = 10 log10( ) the lower UHF band, it can be seen that, the proposed antenna kTsRLp is a potential candidate for Cube satellite communication = Pt,dBm − 30 + Gt,dBi + Gr,dBi − Lp,dB system. − 10 log10 k − 10 log10 Ts − 10 log10 R (1)

TABLE 4. Comparison of characteristics of different UHF antennas.

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TABLE 5. Summary of the link budget analysis of BIRDS 1 CubeSat downlink communication.

Where Pt is transmitted power, Gt and Gr are the transmit V. ANTENNA INTEGRATION AND TESTING WITH antenna gains, Lp is the propagation path loss, k is Boltzman’s SATELLITE BODY constant, Ts is the system noise temperature and R is the The ﬁnal module of the 1U BIRDS-1 satellite Flight Model is data rate. To guarantee the effectiveness of the BIRDS-1 link depicted in Figure 7. A UHF band patch antenna is attached budget analysis, additional terms have contained in the over to the satellite body for transmitting application. After inte- equations to take into account other link losses and to add a gration of the UHF band antenna through non conducting system link margin. Besides for the analysis of the BIRDS-1 glue with the satellite body, different tests were performed in link budget, several potential sources of power loss was incor- the Laboratory of Spacecraft Environment Interaction Engi- porated in the system margin with reasonable estimates. neering (LaSEINE), Kyutech, Japan.

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FIGURE 8. a) Launch conditions: vibration test b) environment conditions: vacuum test and thermal vacuum test.

The upper earth atmosphere contains several unstable ultimate vacuum condition of 10−5 Pa. The thermal cycling particles and free radicals like atomic oxygen due to the chamber, illustrated in Figure 8, periodically varies the tem- high energy radiation from the sun [37]. The atomic oxygen perature from −200 to 200 ◦C at 10−5 Pa. This chamber readily attaches to any metal surface to cause ‘rusting’. tests the structural integrity of the internal circuitry, antennas Thus the antennas were subjected to a high velocity (up to and sensory equipment at the harsh extreme temperatures 10 km/s) jet of atomic oxygen in a test chamber. The stream experienced in LEO operations. Several mechanical and is created using a 5.5 JCO2 laser. The plasma environment vibration stress tests are carried out on the entire satellite encountered in LEO is mimicked in the LEO chamber. The structure to assure, it is with the capacity of withstanding the pressure is maintained at 10−4 Pa to resemble the conditions accelerations and vibrations experienced through the release of upper earth atmosphere. The chamber is equipped with process. Vibration testing exposes the satellite structure to an Electron Cyclotron Resonance plasma source to gener- three types of acceleration, i.e. sine, random and shock, ate about 1012 m−3 plasma density. Furthermore, it uses at varying forces up to 87 kN. No visible cracks were metal halide lamps to evaluate the performance of solar cell observed on the UHF antennas after the rigorous mechanical arrays. Any arcing is detected using the discharge position testing. After the different environmental test of the satellite, identiﬁcation system and the high-speed discharge waveform Long Distance Test, and End to End Test was performed to acquisition system. The primary objective of this chamber verify uplink and downlink communication between satel- is to analyze the performance of the solar cell arrays, com- lite and ground station. Figure 9 shows the long-distance munication antennas and experimental apparatus in low- test setup, EM (Electro-Magnetic) setup Ground station, pressure environments with the presence of plasma. The and the communication test result. The BIRDS-1 Cube- microwave test chamber exposes the satellite prototype to Sat was setup in the inside Takatoyama Park, Japan, and high power microwave from 100 KHz to 10 GHz under Kyutech ground station. The distance between transmitter

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FIGURE 9. (a) BIRDS long-distance test setup (b) BIRDS EM Setup (c) communication test ground station and d) communication test result.

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FIGURE 10. Five BIRDS-1 satellite with two J-SSOD.

FIGURE 11. a) First deployment: Japan (Toki), Ghana (GhanaSat-1), and Mongolia (Mazaalai) b) second deployment: Bangladesh (BRAC Onnesha) and Nigeria (Edusat1). and receiver place was taken 4KM. All the position and Japan. The two long white cases are J-SSOD pods. JEM distance was depicted in Fig.9 with side view and google Small Satellite Orbital Deployer (J-SSOD) is a system for map. The free space path loss at operating frequency during deploying small satellites designed and constructed relative the long distance test was approximately 97 dB. To account to 1U CubeSat design specification that transfers the satellites for additional free space path loss of the orbital altitude, from Japan Experiment Component Kibo’s airlock to the area which is 137 dB, in this long distance test, a 40 dB atten- environment and releases them on orbit. As shown in Figure uator was attached between the base-station antenna and 10, three BIRDS-1 CubeSat’s were in one J-SSOD pod, and receiver. Ground Station sends a command to the BIRDS-1 the other two BIRDS-1 CubeSat’s were in the other J-SSOD EM to perform Digi-Singer, Camera, and POS missions. pod. The J-SSOD is lifted to the ISS on a SpaceX Falcon Upon receiving the mission data, the ground station measured 9 CRS-11 rocket from John F. Kennedy Space Center, USA the signal strength and successfully decoded the mission on June 3, 2017. Finally, five ‘‘BIRDS project’’ CubeSat’s data. were successfully deployed into orbit from the Japanese Experiment Module ‘‘Kibo’’ of the International Space Sta- tion (ISS) on 7 July 2017 which is shown in Figure 11. VI. BIRDS SATELLITE LAUNCHING IN LEO On 8 July 2017, the amateur radio community certified After completing the flight model of five 1U BIRDS, that all BIRDS-1 satellites are active which is depicted in the satellites were handed over to JAXA Tksuba center, Figure 12.

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FIGURE 12. (a) Status of the active 1U BIRDS Satellites on UHF Band Frequencies (b) BIRDS-1 CW beacon signals visually displayed by DK3WN (Mike in German).

VII. CONCLUSION long distance communication test in LASINE lab, Kyutech, A compact UHF band patch antenna system compatible with Japan. Finally, the five 1U BIRDS satellite were successfully 1U BIRDS-1 CubeSat constellation has been presented in deployed in LEO from BIRDS-1 satellites on 7 July 2017 at this paper. The antenna has been designed on the basis of the J John F. Kennedy Space Center, Florida, USA. The the specifications of the 1U BIRDS satellite mission but is preliminary mission for this CubeSat is Earth observation by suitable for more general cases. The antenna consists of a a COTS camera and Outreach through Digi-Singer, a sound folded meander line patch, shorting pin and partial ground relaying COTS device. UHF amateur radio band has been plane with coaxial probe fed and it is realized in a planar used while interlinking the ground station of five countries. technology achieving a compact size, low profile and geometric characteristics. A prototype of the proposed antenna has been realized. The measurements of the fabricated antenna in ACKNOWLEDGMENT an anechoic chamber, in terms of impedance matching and The authors would also like to thank the BIRDS-1 team radiation pattern, show a good agreement with simulation member and Laboratory of Spacecraft Environment Interac- results. The antenna was also mounted with BIRDS satellite tion Engineering (LaSEINE), Kyutech, Japan to provide the body structure and tested in different environmental test and facilities for developing, testing and launching in the space.

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Constantinou, ‘‘A compact microstrip antenna ing from Islamic University, Kushtia, Bangladesh, with tapered peripheral slits for CubeSat RF payloads at 436MHz: Minia- in 2005 and 2007, respectively, and the Ph.D. turization techniques, design & numerical results,’’ in Proc. IEEE Int. degree from Universiti Kebangsaan Malaysia, Workshop Satellite Space Commun. (IWSSC), Oct. 2008, pp. 255–259. Malaysia, in 2015. From 2008 to 2011, he was [15] C. Kakoyiannis and P. Constantinou, Electrically Small Microstrip Anten- a Lecturer at Patuakhali Science and Technology nas Targeting Miniaturized Satellites: The Cubesat Paradigm. Rijeka, University, Bangladesh, where he was an Assis- Croatia: InTech, 2011. tant Professor from 2011 to 2015. He is currently [16] S. K. Podilchak et al., ‘‘Compact antenna for microsatellite using folded as an Associate Professor at Patuakhali Science and Technology Univer- shorted patches and an integrated feeding network,’’ in Proc. 6th Eur. Conf. sity. 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VOLUME 6, 2018 54293 M. Samsuzzaman et al.: BIRDS-1 CubeSat Constellation Using Compact UHF Patch Antenna

MOHAMMAD TARIQUL ISLAM (SM’08) is MENGU CHO received the B.S. and M.S. degrees a Professor at the Department of Electrical, from the Department of Aeronautics, University of Electronic and Systems Engineering, Universiti Tokyo, Tokyo, Japan, in 1985 and 1987, respec- Kebangsaan Malaysia (UKM) and a Visiting Pro- tively, and the Ph.D. degree from the Department fessor with the Kyushu Institute of Technology, of Aero/Astro, Massachusetts Institute of Tech- Japan. He has authored and co-authored about nology, Cambridge, MA, USA, in 1992. From 350 research journal articles, nearly 165 confer- 1992 to 1995, he was a Research Associate with ence articles, and a few book chapters on various Kobe University, Kobe, Japan. From 1995 to 1996, topics related to antennas, microwaves, and elec- he was a Teaching Associates with International tromagnetic radiation analysis with 16 inventory Space University, France. Since 1996, he has been patents ﬁled. Thus far, his publications have been cited 4210 times and his with the Kyushu Institute of Technology (KIT), Japan, where he was an H-index is 33 (Source: Scopus). His Google scholar citation is 5545 and Assistant Professor in 1996 and an Associate Professor in 1997. Since 2004, H-index is 36. His research interests include communication antenna design, he has been a Professor and also the Director of the Laboratory of Spacecraft radio astronomy antennas, satellite antennas, and electromagnetic radia- Environment Interaction Engineering, KIT. He has been with the Department tion analysis. He was a recipient of over 40 research grants from the of Applied Science for Integrated System Engineering since 2010. He has Malaysian Ministry of Science, Technology and Innovation, Ministry of authored or co-authored more than 120 papers in peer-reviewed journals. His Education, UKM research grant, international research grants from Japan research interests include spacecraft environmental interaction, especially and Saudi Arabia. He was a recipient of the several International Gold spacecraft charging and nano-satellite reliability. Medal awards, a Best Invention in Telecommunication Award, a Special Award from Vietnam for his research and innovation, and Best Researcher Awards in 2010 and 2011 at UKM. He also won the Best Innovation Award in 2011 and the Best Research Group in ICT Niche in 2014 by UKM. He was a recipient of the Publication Award from Malaysian Space Agency in 2014, 2013, 2010, 2009 and the Best Paper Presentation Award in 2012 Interna- tional Symposium on Antennas and Propagation, (ISAP 2012) at Nagoya, Japan, and in 2015 in IconSpace. He is a Chartered Professional Engineer- CEng, a member of IET (U.K.), and a member of IEICE (Japan). He is currently an Editor-in-Chief of the International Journal of Electronics and Informatics, and an Associate Editor of Electronics Letter.

SALEHIN KIBRIA was born in Dhaka, Bangladesh, in 1988. He received the B.Eng. (Hons.) degree in electronics majoring in telecommunications from Universiti Kebangsaan Malaysia (UKM), Malaysia, and the M.Sc. degree in electronics majoring in telecommunications from Multimedia University. He is currently pur- suing the Ph.D. degree with UKM. He was a Research Assistant with the Faculty of Engi- neering and Built Environment in a research project funded by Malaysian Government. His research interest focuses on microwave imaging, RFID systems, and heuristic optimization techniques.

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