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Ssc16-Iii-05 SSC16-III-05 One-year Deep Space Flight Results of the World’s First Full-scale 50-kg-class Deep Space Probe PROCYON and Its Future Prospects Ryu Funase, Takaya Inamori, Satoshi Ikari, Naoya Ozaki, Shintaro Nakajima, Kaito Ariu, Hiroyuki Koizumi Department of Aeronautics and Astronautics, The University of Tokyo, Japan Hongo 7-3-1, Bunkyo-ku, Tokyo 113-8656, Japan; +81-3-5841-0742 [email protected] Shingo Kameda Department of Physics, College of Science, Rikkyo University, Japan Nishi-Ikebukuro 3-34-1, Toshima-ku, Tokyo 171-8501, Japan; +81-3-3985-2617 Atsushi Tomiki, Yuta Kobayashi, Taichi Ito, Yasuhiro Kawakatsu Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Japan Yoshinodai 3-1-1, Sagamihara-shi, Kanagawa 229-8510, Japan; +81-50-3362-6575 ABSTRACT This paper reports the one-year deep space flight results of the 50-kg-class deep space exploration micro-spacecraft PROCYON, which was jointly developed by the University of Tokyo and the Japan Aerospace Exploration Agency. PROCYON was developed with a very low cost (a few million dollars) and within a very short period (about 1 year), taking advantage of the heritage from Japanese Earth-orbiting micro-satellite missions. PROCYON was launched into an Earth departure trajectory together with the Japanese second asteroid sample return spacecraft Hayabusa-2 on December 3, 2014. During its one-year deep space flight, PROCYON succeeded in the demonstration of a 50-kg- class deep space exploration bus system, which includes a GaN-based SSPA (Solid-State Power Amplifier) with the world’s highest RF efficiency; the demonstration of a novel DDOR (Delta Differential One-way Range) orbit determination method; and the world’s first demonstration of a micro propulsion system with both trajectory and attitude control capabilities in deep space. Scientific observation by a Lyman alpha imager was also successfully conducted. These successes demonstrate the capability of this class of spacecraft for performing a deep space mission by itself and also demonstrated that it can be a low-cost and flexible tool for future deep space exploration. INTRODUCTION primary mission (the demonstration of a 50-kg-class deep space exploration bus system), and also achieved Recently, a number of organizations such as governmental space agencies, private companies, and some of its optional missions, which are the universities are planning to build nano-satellites (1–10 demonstration of advanced deep space exploration technologies and scientific observations. These kg) and micro-satellites (~50 kg) for deep space exploration [1,2]. This effort is expected to establish a successes demonstrated the capability of this class of low-cost and flexible tool for deep space exploration, spacecraft for performing a deep space mission by itself and also demonstrated that it can be a useful tool for and these ultra-small spacecraft will play a significant role in future solar system exploration. deep space exploration. As the first step of these attempts, the Intelligent Space MISSION OF PROCYON Systems Laboratory (ISSL) at the University of Tokyo The primary mission of PROCYON is the and the Japan Aerospace Exploration Agency (JAXA) demonstration of a micro-spacecraft bus system for developed and launched the 50-kg-class deep space deep space exploration, which is intended to show that exploration micro-spacecraft PROCYON (PRoximate a spacecraft of this scale (~50 kg) can conduct a deep Object Close flYby with Optical Navigation), which space mission by itself. The secondary missions became the world’s smallest full-scale deep space probe (advanced missions) consist of engineering and ever. PROCYON was launched together with the scientific missions to advance or utilize deep space Japanese second asteroid sample return spacecraft exploration. The engineering mission includes the low- Hayabusa-2 [3] on December 3, 2014. During its one- thrust deep space maneuver for performing an Earth year flight in deep space, PROCYON succeeded in its swing-by and changing the trajectory to flyby a Near- Funase 1 30th Annual AIAA/USU Conference on Small Satellites Earth asteroid and high-resolution observation of a Near-Earth asteroid during a close (<30 km) and fast (~10 km/s) flyby. The scientific mission is the wide- view observation of geocorona with LAICA (Lyman Rotate Alpha Imaging Camera) [4] from a vantage point outside Earth’s geocoronal distribution. +Z Fig. 1 shows the trajectory of PROCYON, which is +X +Y launched with Hayabusa-2 and initially inserted into an Earth resonant trajectory that allows the spacecraft to return to Earth by solar electric propulsion. Within several months after launch, the primary mission (demonstration of the bus system) is conducted. Then, a DSM (Deep Space Maneuver) using its miniature ion propulsion system is conducted so that the spacecraft Figure 2: Close flyby observation of an asteroid by will return to Earth for swing-by which will direct the the onboard image feedback control spacecraft’s trajectory to its target asteroid, 2000 PROCYON SYSTEM CONFIGURATION DP107 [5]. PROCYON is intended to perform close flyby trajectory guidance by optical navigation and will The external view of PROCYON is shown in Figs. 3, 4, pass within 30 km of the asteroid. The flyby velocity and 5. Fig. 6 shows the system block diagram of will be less than 10 km/s relative to the target asteroid. PROCYON, and the specifications of the spacecraft are During the close flyby, automatic tracking observation listed in Table 1. Most of the bus system of PROCYON of the asteroid will be conducted using a camera with a is based on that of a 50-kg-class Earth-orbiting micro- scan mirror and onboard image feedback control, which satellite, excluding the communication [6] and enables a LOS (Line of Sight) maneuver while propulsion [7] systems, which were newly developed maintaining the spacecraft’s attitude (Fig. 2). for the deep space mission. Solar Array Panel X-band HGA X-band LGA for Uplink (SAP) X-band LGA for Downlink Cold Gas Jet Thruster Cold Gas Jet Thrusters +Z +Y +X X-band MGA Ion Thruster Non-spin Sun Aspect Sensor Cold Gas Jet Thrusters (NSAS) Figure 3: External view of PROCYON (top view) Cold Gas Jet Thrusters Telescope Star Tracker X-band MGA X-band LGA +Z for Downlink +X +Y X-band LGA for Uplink Cold Gas Jet Thrusters Figure 1: Trajectory design of PROCYON (Top: Sun-centered J2000 EC, Bottom: Sun–Earth fixed Figure 4: External view of PROCYON (bottom rotational frame) view) Funase 2 30th Annual AIAA/USU Conference on Small Satellites AOCS Thermal control MIPS HTR(xN) FOG STT SS(x5) RW(x4) +XeCGJ EPS HRM(x4) PDU MIR TELE SCOPE SAP(x4) PCU OBC IMG+PROC BAT (Data Handling) LAICA LGA Mission XRX Power I/F BPF XSW3 LGA XSW4 Data I/F XTRP LGA XTX BPF XSW1 LGA MGA XSW2 TX XSSPA XDIP VLBI XSW5 XHYB HGA Communication Figure 6: System block diagram of PROCYON venture companies as key development policies. The total mass of the fabricated onboard telecommunication system was only about 7.3 kg excluding the RF coaxial harness. The total power consumption during two-way operation with 15 W of RF output power at the SSPA was only about 54.3 W using a GaN SSPA with the world’s highest RF efficiency (average efficiency: 33.7%) [8]. Propulsion System for Attitude and Orbit Control A micro propulsion system named I-COUPS (Ion thruster and COld-gas thruster Unified Propulsion System) was also newly developed for PROCYON [7]. Figure 5: External view of the PROCYON flight The propulsion system unified an ion thruster and cold- model (solar array panels stowed) gas thrusters by sharing a single gas system to provide these propulsive capabilities with a limited mass and Communication System volume. The ion thruster provides 300 μN of thrust with a specific impulse of about 1000 s, which is used for a A low-cost miniaturized X-band onboard DSM. The cold-gas thrusters, which provide about 20 telecommunication system compatible with CCSDS mN of thrust with a specific impulse of 24 s, are used (The Consultative Committee for Space Data Systems) for both reaction wheel desaturation and the asteroid recommendations was newly developed. The flyby trajectory correction maneuver. The weight of the communication system of PROCYON consists of an propulsion system is less than 10 kg including about 2.5 XTRP (X-band Transponder), a high-power (15-W kg of propellant (Xenon). output) GaN-based SSPA (Solid-State Power Amplifier), a tone generator for the DDOR (Delta The components and structures of I-COUPS were based Differential One-way Range) orbit determination, on the miniature ion propulsion system MIPS [9,10], isoflux LGAs (Low-gain Antennas), flat antennas which was developed for the 60-kg LEO satellite (MGA and HGA), and other passive components Hodoyoshi-4 [11,12]. The difference from MIPS is the (switches, a diplexer, and band-pass filters). addition of a cold-gas thruster system whose gas is extracted from the existing xenon gas system. The We focused on adopting only COTS products including power consumption is 7.3 W in its standby mode, 11.5 a GaN HEMT, conducting appropriate space W during the operation of two cold-gas thrusters, and environmental testing, and balancing the in-house 40.0 W during the operation of the ion thruster. development and cooperation with competent small Funase 3 30th Annual AIAA/USU Conference on Small Satellites Table 1: Specifications of PROCYON Structure Size 0.55m × 0.55m × 0.67m + 4 SAPs (Solar Array Panels) Weight <70 kg (wet) Power SAP Triple Junction GaAs,
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