A5044200152- Spacecraft Design and Technology
- Plasma Diagnostics and Applications
- Spacecraft and Cryogenic Technologies
- Astro and Planetary Science
- Electrohydrodynamics and Fluid Dynamics
- Rocket and propulsion systems research
- Diamond and Carbon-based Materials Research
- Space Satellite Systems and Control
- Planetary Science and Exploration
- Ion-surface interactions and analysis
- Energy Harvesting in Wireless Networks
- Laser-induced spectroscopy and plasma
- Energetic Materials and Combustion
- Opportunistic and Delay-Tolerant Networks
- solar cell performance optimization
- Muon and positron interactions and applications
- Advanced Materials Characterization Techniques
- Gas Dynamics and Kinetic Theory
- Spacecraft Dynamics and Control
- Advanced Aircraft Design and Technologies
- Cryptographic Implementations and Security
- Nuclear Physics and Applications
- Satellite Communication Systems
- Particle accelerators and beam dynamics
- Human Motion and Animation
The University of Tokyo
2014-2020
Toshiba (Japan)
2018
Initial flight operations of the miniature propulsion system I-COUPS (Ion Thruster and COld-gas Unified Propulsion System) are presented with problems found in space its countermeasures for them. The was developed by University Tokyo installed on a 70 kg probe, PROCYON as main to verify propulsive capability first micropropulsion deep space. successfully launched December 3rd, 2014 inserted into an orbit around Sun. PROYON project team started operation interplanetary orbit. Up today,...
EQUULEUS (EQUilibriUm Lunar-Earth point 6U Spacecraft) will be the world's smallest spacecraft to explore Earth-Moon Lagrange point. It is being jointly developed by JAXA (Japan Aerospace Exploration Agency) and University of Tokyo, launched NASA's Space Launch System Mission-1. The fly a libration orbit around L2 (EML2) demonstrate low-energy trajectory-control techniques within Sun-Earth-Moon region for first time nano-class spacecraft. also carries three scientific observation missions:...
In this study, a water resistojet propulsion system, named AQUARIUS, is proposed and the breadboard model (BBM) test results engineering (EM) design are described.AQUARIUS will be on-boarded SLS EM-1 CubeSat: EQUULEUS, which scheduled to launch in 2019.AQUARIUS uses storable, safe non-toxic propellant: water, allows for of all system below 100 kPa, reduction dry mass ratio simplification feed line routing using soft tubes.AQUARIUS consists three components as follows: tank, vaporization...
This study proposes a micropropulsion system unifying ion thrusters and resistojet assessing that propulsive capability. The remarkable features of the are usage water propellant unification two types by single propellant. Water has been regarded as an attractive in view points safety, availability, handling ability, low molecular mass, future procurement space. A multimode propulsion is solution for increasing demand nano-/microsatellite missions. proposal to use microwave discharge...
The University of Tokyo has proposed a water resistojet thruster with high certainty liquid–vapor separation and low power consumption. In this propulsion system, liquid is periodically vaporized in pulsating manner to generate thrust. A vaporization chamber labyrinth-shaped flow path catches droplets using their surface tension separate the vapor, vaporize under normal temperature reduce input by reusing heat from surrounding components. study, we designed fabricated flight model system for...
This paper presents the development of a thrust stand to enable direct measurement and specific impulse for CubeSat propulsion system during firing. The is an inverted pendulum incorporates mass balance in situ measurement. proposed calibration procedure allows precise performance characterization achieves resolution 80 μN 0.01 g loss, by taking into account drift thrust-stand zero caused propellant consumption. water micro-resistojet CubeSats was directly characterized as proof concept...
This study proposes the laser-ignited micromotor (LIMO), which is a new propulsion system for CubeSats to overcome problems associated with conventional chemical propellants. The solid propellant pellets are stacked and stored in micromotor. concept makes it possible design total impulse of flexible manner at low cost short time, depending on microsatellite missions. In addition, laser-ignition integrated address ignition delay difficulty cutting high-current feed lines system. Firing tests...
The AQua Thruster-Demonstrator (AQT-D) is a 3U CubeSat for demonstrating the water resistojet propulsion system developed by University of Tokyo. AQT-D was launched to rendezvous with International Space Station (ISS) in middle 2019. This spacecraft will also be world's first ISS-deployed equipped system. comprised 1U and 2U bus systems. systems were designed based on TRICOM-1R, known as "Tasuki," using SS-520 nanosatellite launcher operation during 2017-2018. AQUA ResIstojet propUlsion...
The element and/or material dependence of the useful yield in laser-ionization sputtered neutral mass spectrometry (SNMS) using a high-photon-flux laser was investigated. Useful yields obtained from Si, B, As, and O Si SiO2 matrices both secondary ion (SIMS) SNMS were compared, possibility accurate analysis impurities multilayers investigated terms tunnel ionization. behavior atoms released surface by bombardment calculated, it considered that flying speed depends on this causes elemental...
A micro-solid rocket as the propulsion system for 1–10 kg-class micro-spacecraft is proposed here. The uses a boron/potassium nitrate pellet propellant and its total impulse about 1.5 Ns. Higher needed on small spacecraft to perform advanced space missions such sample return, formation flight, active debris removal. To increase impulse, it necessary mass. However, there difficulty in producing new sizes of solid propellant. author designed 20–50 Ns-class which stack existing multiple B/KNO3...
We propose thrust vector management by correctly positioning the thruster on a spacecraft measurement to decrease unwanted torque of misalignment. A ground test was performed measure 2-dimensional ion current distribution 10W-class miniature electrostatic probe. The showed that inclining angle 1.4º from geometrically symmetric axis thruster. positioned first interplanetary micro-spacecraft: PROCYON after redesigning bracket. Thrust estimation in initial on-orbit operation 6.5 hours passes...
A new laser ionization method for sputtered neutral mass spectrometry (SNMS), which the authors call “dual-laser SNMS,” was developed to increase probability and improve sensitivity. In this technique, pulsed IR UV lasers irradiated atoms simultaneously, while additional pulse enhanced process. The useful yields of target elements increased by 10%–20% compared using irradiation alone, yield with increasing power. addition, there little correlation between potential ratio enhancement....
Today, the need for micropropulsion systems micro- and nanospacecraft is growing. Micro-nozzles generally lead to low Reynolds numbers nozzle flow. It has been reported that efficiency was decreased at region. However, there were gaps of efficiencies same number in previous researches, ambient pressure suggested as one possible cause gaps. In this study, performance measured by changing throat ranged from 50 800. As a result, it shown leads high only under 200. affected both pressure.
A laser-ignition micro solid rocket for application as propulsion on a 1-10 kg-class microspacecraft was proposed and designed. The uses boron/potassium nitrate propellant, number of propellant blocks are ignited by irradiating their surface with 1 W diode laser through laser-incident window. According to previous experiments, contamination the window can cause ignition failure high 39% (7 thrusters out 18) result gas generated at initial phase irradiation. To reduce this contamination,...
A micro-thruster using stacked solid propellant pellets for nano-satellites has the high versatility. This thruster can generate arbitrary total impulse by changing number of installed pellets. In order to install in a nano-satellite, it is necessary clarify conditions stable operation. We changed materials and manufacturing methods thruster, measured combustion chamber pressure burning rate. certain condition achieved difference between rates pins caused unexpected rise. silicone rubber...
In this paper, we proposed Inter-satellite laser power transmission service and indicated its feasibility from the viewpoint of both technology business. Solar-pumped allows for between 24 satellites at an altitude 300 km 1800 assuming that some energy conversion efficiency beam efficiency. If could be developed with initial cost 7.97 billion yen, operational one 10 thousand yen/hour, a development period five years, recovered in 14th year launch benefit 55 yen can achieved during 15 years...