LiteBIRD System Definition Masashi Hazumi (KEK and Kavli IPMU) December 14, 2015
LiteBIRD working group 128 members, interna/onal and interdisciplinary (as of Dec 14, 2015) U. Tsukuba JAXA Osaka Pref. U. KEK NAOJ APC Paris UC Berkeley / H. Fuke M. Inoue M. Hazumi (PI) A. Dominjon M. Nagai R. Stompor LBNL I. Kawano K. Kimura M. Hasegawa J. Inatani D. Barron H. Matsuhara M. Kozu N. Kimura K. Karatsu TIT Paris ILP J. Borrill T. Matsumura H. Ogawa K. Kohri S. Kashima S. Matsuoka Y. Chinone J. Errard K. Mitsuda N. Okada H. Morii T. Nitta A. Cukierman R. Chendra T. Nishibori T. Nagasaki T. Noguchi T. de Haan CU Boulder Okayama U. K. Nishijo R. Nagata S. Sekiguchi N. Goeckner-wald Tohoku U. N. Halverson A. Noda H. Nishino Y. Sekimoto H. Ishino P. Harvey M. Hattori A. Okamoto S. Oguri S. Shu A. Kibayashi C. Hill T. Morishima McGill U. S. Sakai T. Okamura Y. Kibe Y. Hori M. Dobbs Y. Sato N. Sato Saitama U. Y. Kida W. Holzapfel Nagoya U. K. Shinozaki T. Suzuki A. Okamoto M. Naruse O. Jeong K. Ichiki MPA H. Sugita O. Tajima Y. Yamada R. Keskitalo E. Komatsu Y. Takei T. Tomaru NICT T. Kisner Yokohama M. Utsunomiya M. Yoshida A. Kusaka NIFS Y. Uzawa Natl. U. NIST T. Wada A. Lee(US PI) S. Takada T. Fujino G. Hilton N. Yamasaki E. Linder SOKENDAI Konan U. F. Irie J. Hubmayr T. Yoshida P. Richards Kavli IPMU Y. Akiba I. Ohta K. Mizukami K. Yotsumoto U. Seljak K. Hattori Y. Inoue S. Nakamura Stanford U. B. Sherwin H. Ishitsuka U. Tokyo N. Katayama K. Natsume S. Cho Osaka U. A. Suzuki H. Sugai Y. Segawa N. Tomita T. Yamashita K. Irwin P. Turin S. Kuromiya H. Watanabe S. Kernasovskiy B. Westbrook Kansei M. Nakajima RIKEN C.-L. Kuo N. Whitehorn S. Takakura Gakuin U. S. Mima D. Li K. Takano S. Matsuura C. Otani T. Namikawa W. Ogburn UC San Diego JAXA engineers X-ray CMB experimeters T. Elleot astrophysicists U. Wisconsin B. Keating K. Arnold G. Rebeiz Super-conducting IR astronomers detector developpers 2 2015/12/14
Outline Note there was a talk on Mission Definition on Saturday Dec. 12. 1. Recap of Mission Definition 2. Summary of Pre-phase-A Studies 3. Phase-A Overview This talk is an introduction to many specific technical talks that will be given in this workshop. 3 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
1. Recap on Mission Definition 4 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
Talk on Dec. 12 LiteBIRD Mission Summary Lite (Light) Satellite for the Studies of B-mode Polarization and Inflation from Cosmic Background Radiation Detection • CMB B-mode satellite proposed to JAXA – Also to NASA for US participation – Both proposals passed initial selection • Proposed launch year: JFY 2022 • Mission Requirements – Total uncertainty on r < 0.001* – Multipole coverage: 2 ≤ l ≤ 200 • Each bump (reionization, recombination) with >5sigma if r > 0.01 *Our current studies yield • Orbit: L2 σ (r) = 2 x 10 - 4 (for r=0) • Observing time: 3 years for 3 year observation 5 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
15 frequency bands as global Phase-A baseline Polarization sensitivity 2.4 µ Karcmin 10 − 4 CO J10 CO J21 CO J32 CO J43 (3 year operation, Synchrotron including margin) LFT Sensitivity [K] 10 − 5 HFT HFT t s u D CMB LFT 10 − 6 40 100 400 Frequency [GHz] 6 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
LiteBIRD constraints on r vs. n s plane (15 bands) 7 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
2. Summary of Pre-phase-A Studies 8 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
LiteBIRD Instrument Multi-chroic focal plane • Mission module benefits from heritages of other detectors missions (e.g. ASTRO-H) and ground-based experiments (e.g. POLARBEAR). • Bus module based on high TRL components Continuously- Lenslet rotating half wave Line of sight 0.1rpm plate (HWP) FOV 10 x 20 deg. spin TES MKID rate 30 deg. Mission module Cryogenics slip ring n JT/ST and ADR (ASTRO-H S o l a heritage) r a r r a y p a d d Mirrors at 4K l e Bus module HGA : X band data transfer to the ground 9 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
LiteBIRD block diagram 1.8m TES option Low Temp. Mission Instruments Warm Mission Instruments Bus System Fit in H2 envelope 10 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
Scan strategy at L2 Sun Precession angle α = 65° 90 min. Spin angle β = 30° 0.1rpm Anti-sun direction 11 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
Scan strategy α + β ≥ 90° for full sky α + β ≤ 95° from thermal/ optical requirements ( α 、 β ) = ( 65°,30° ) chosen LiteBIRD to minimize the effect of E to B leakage due to pointing bias Good crosslink reduces Scan path pointing bias w/ multiple measurements 12 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
Operation concept LiteBIRD'satellite � Open'data'to'the'world' � Each'new'GN'sta+on' (Tsukuba)' Manage/opera+on' Orbital'mechanics'' of'all-sky'map'data � System'(Tsukuba) � 3.6GByte/day Data'management'center' Mission'observa+on' JAXA'DARTS'etc.'(TBD) � Ground'sta+on'S-band' data,'HK,'poin+ng' (Uchinoura'34m'or'' HK'monitor'in' data,'ranging,'' Uchinoura'20m)' satellite,'aNtude' X-band'10Mbps � control,'ranging,' Scien+fic'results � refrigerator'P'HWP' opera+on � Ground'sta+on'X-band' Data'recep+on'request � (Usuda'64m'or' Observed'data'storage/' Data'process'based' Uchinoura'34m) � Transport'to'data' on'calibrated'data � Raw'data' analysis'center � Data'analysis'center'' Gnd.'control'sta+on' U'of'Tokyo,'Kavli'IPMU � Sagamihara'SSOC' 13 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
Road to achieve the full success Statistical Systematic σ ( r ) < 0.001 Foreground Lensing Observer bias as the 5 th element à mitigation by e.g. blind analyses 14 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
LiteBIRD Sensitivity (15 bands) J. Errard σ (r) = 0.45 x 10 - 3 for r = 0.01, including foreground removal*, cosmic variance and delensing w/ CIB** This proposal r < 0.4 x 10 - 3 (95% C.L.) polarized dust @ 95GHz polarized synchrotron p=15%, f sky =65% @ 95GHz, p=15%, for undetectably small r f sky =65% Note: σ (r=0) = δ r = 2 x 10 - 4 r=0.1 R. Nagata σ sys (total) = 1.1 x 10 - 4 r=0.01 Source Expctd. error Reasoning This Pointing 0.23 arcmin Star tracker spec. proposal Angle calibration 1 arcmin C l EB method Absolute gain 0.6% CMB dipole Diff. gain 0.43% * Foreground residual estimation with Errard et al. 2011, Phys. Rev. D Diff. beam width <1% Optical 84, 063005 simulation, HWP Diff. ellipticity <1% plus a new method (this proposal, another paper in preparation) experience ** ”Delensing the CMB with the Cosmic Infrared Background”, B. D. Diff. pointing <1% Sherwin, M. Schmittfull arXiv:1502.05356 15 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
Top-level system requirements Mission Requirements System Requirements M1 All-sky CMB S1.1 Total CMB polarization observation S1 Sensitivity observing time S2 δ r breakdown S2.1 Pol. modulation M2 Dust observation S3 # bands S3.1 Bandwidth M3 Synchrotron observation S4 Angular resolution M4 δ r < 0.001 S5 Linear pol. meas. M5 Power specttrum � S6 CO separation C1 Launch vehicle Prerequisits Constraints P1 Observation in space C2 Cost P2 Foreground removal C3 Schedule P3 Operation C4 Competition 16 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
Launch Vehicle H3 • First test launch in 2020 • ½ cost w/ same capability (comparison w/ H-II B) 17 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
3. Phase-A Overview 18 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
JAXA initial phases of space science missions LiteBIRD Reviews System Definition Review System Requirements Review The current design for Phase A studies Mission is regarded as an example, which is Definition subject to modifications. Review 19 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
Systems Engineering of LiteBIRD Reviews System Definition Documents • MDR documents Mission • Design specifications • System Requirements Requirements • Verification plans and criteria • SEMP Documents • Interface definitions • Risk identification/mitigation Architecture Design System Mission Requirements Functional Design Requirements Analysis Definition Physical Design 20 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
T esting and integrations POLARBEAR2 integration is ongoing at KEK with sub-K cryogenic system and UC Berkeley TES bolometers. LiteBIRD has JAXA 13-m diameter members with the space chamber CMB instrument integration expertise, Astro-H test is done satellite integration here. expertise, HEP radiation expertise together with the fully equipped facilities. Proton irradiation tests at HIMAC JAXA 1-m diameter space 21 chamber JAXA 6-m diameter space chamber December 14, 2015
Provisional Phase-A Timeline in 2016 2015 2016 9 10 11 12 1 2 3 4 5 6 7 8 9 10 11 12 Phase-A1 ISAS/JAXA Review SRR NASA Phase-A Evaluation CSR 22 Masashi Hazumi (KEK, Kavli IPMU) 2015/12/14
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