Nano-JASMINE project

Transcription

1 Nano-JASMINE project NAOJ Y. Kobayashi Overview nj project Plan of talk Aim of nj project Historic facts Collaboration with University of Tokyo Telescope and CCD Observation along great circle Cosmic radiation on CCD Attitude control Science -> Nishi Data Analysis -> (Yamada) Nano-JASMINE satellite flight model 2010

2 Aim of nj Project Goal of JASMINE project astrometry of entire Galaxy in infrared dust obscured stars Aim of nano-jasmine project To get satellite experience quick, cheap, easy Not to be behind Gaia Launch cost $10000/kg $100000$ Not quick or easy, but cheap 10 years anniversary in 2013

3 Current Status Quick, Easy, Cheap Not easy or quick, but cheap High requirements (ex. Attitude control or temperature stability) Similar components (power, attitude control, communication, Computer, GPS, data strage, houskeeping ) Similar tests (vibration, radiation, mass, impact, thermal structure, alignment ) Handmade many parts parts are small Got much experience Cost limitation

4 Historical Facts Weight and size Name of Nano-JASMINE Initial estimate was less than 10 kg Cyclone-4 launcher capacity >5 ton High requirement Hipparcos (Gaia) type observation Two beam and great circle scan Old JASMINE was Hipparcos Type Sat. technical demonstration Femto kg Pico kg Nano 1-10 kg Micro kg Mini kg Medium kg Large > 1000 kg JASMINE and small-jasmine Small JASMINE -> limited area -> HgCdTe -> Single Field Femto satellite Sprite

5 Nakasuka labo cube sat + PRISM ~ Gaia-JASMINE joint meeting Collaboration with ISSL Cooperation with UT group leaded by Nakasuka Possibility of very small satellite Responsible fro bass system and mission management Prof. Nakasuka Students and graduate students technology transfer keep technology of launch ready satellite Cubesat XI-IV ~

6 Events chart Cyclone-4 CHEOPS Start CDR1 CDR2 thermal CDR3 BBM EM structure test FM operation test AR15 AR16

7 Telescope and Sensor 5.4(eD 5.0cm) cm Richey-Chretien telescope all aluminum gold over coating Two beam configuration angle 99.6 FDCCD Subaru Hyper Suprime Cam Thickness 200um high back bias radiation cooling and pertier cooler for telescope F=33 (f=167cm) FOV 0.5 Cut on 0.59um filter Beam-combiner M1 M2 M5 M4 M3

8 Observation Low Earth Orbit ~800 km Sun-synchronous orbit Spin axis Rotation/60days 45 to Sun Scan by Spinning and TDI observation Whole sky/6 month 5x7 pixels image down load fov 0.5 deg. 1.75sec / pixel diffraction limit 3.8 arcsec x 2-4 mag saturation up to 7.5mag stars 3mas up to 9 mag stars 2 years observation Red : sun Green: Spin axis Orange: Fov

9 Cosmic radiation on CCD PSF distortion due cosmic radiation on CCD To estimate PSF on orbit Proton irradiation experiment Transfer Efficiency Trap and release CCD PRF measurement parameters of physical model F temperature Vbb diffusision drift Simulation PSF Proton irradiated FDCCD Charge transfer

10 PSF estimation Measure Relations of PRF and Physical Parameters Star + PRF + Charge Transfer + tracking, vibration brighter flatter effect

11 Attitude Sensors and Actuators Sensors: Fiber Optical Gyro, Star Trucker, Magnetic Sensor, Sun Sensor, Silicon Gyro) Actuator: Magnetic Torquer, Magnetic Canceler, Reaction Wheel) 3-axis attitude control Parameter estimate on orbit Satellite scaling law Magnetic Disturbance >> Atmospheric Disturbance > Reaction Wheel Magnetic Sensor Magnetic Torqer Sun Sensor Fiber Optical Gyro Star Trucker

12 Attitude Control Seaquential Attitude Control after Launching 1. Initial control 20 deg. magnetic sensor -> MTQ 2. Coarse control 2 deg. magnetic sensor, sun sensor, FOG -> MTQ (MC) 3. Fine control 0.1deg. STT FOG -> RW, MC 4. Observation mode 740mas/8.8s nj image -> RW, MC offset tracking

13 Conclusion Still looking for launch chance Got much experience of satellite mission nj is/was good project