We present the development of a breadboard model achromatic half-wave plate (AHWP) for the LiteBIRD Low-Frequency Telescope (LFT). LiteBIRD is a JAXA-led strategic L-class satellite mission to probe the cosmic microwave background polarization. The breadboard model (BBM) polarization modulator unit (PMU) of the LFT uses an AHWP, which achieves an observational frequency coverage 34-161 GHz using a five-layer sapphire stack with a diameter of 330 mm based on the Pancharatnam recipe. The sub-wavelength structures on both end surfaces mitigate the reflection over broadband frequencies. The designed single sapphire plate thickness is 4.95 mm, with a corresponding half-wave shift center frequency of 97.5 GHz. We use hydro-catalysis bonding to glue the sapphire surfaces and assemble the five-layer AHWP. The AHWP is successfully assembled and measured. The transmittance and polarization properties are consistent with the theoretical prediction that neglects the effect of the bonding interfaces. In this work, we present the AHWP design, the assembly process, and the polarimetric characterization. We also discuss the path-forward for this BBM AHWP including the cryogenic and vibrational tests, and the development plan for the flight-size engineering model.
LiteBIRD is an JAXA-led strategic L-class satellite mission designed to measure the primordial B modes of the cosmic microwave background radiation (CMB) to test cosmic inflation. The LiteBIRD Low-Frequency telescope employs a polarization modulator unit (PMU). The PMU is placed at the telescope aperture to modulate the incoming CMB polarization signal by using a continuous rotating half-wave plate to reduce the impact of 1/f noise and differential systematic effects. The current PMU design employs three cryogenic holder mechanisms that hold the rotor until the superconducting magnet bearing cools below its critical temperature after launch. They also serve a conductive path to the rotor when they are held. Minimizing the heat dissipation of this holder is one of the key development goals of the PMU due to the limited cooling power on the satellite system. In this paper, We report on the detailed design of the holder and the developed cryogenic stepping motor that actuates the holder. Also, we conducted the preliminary thermal characterization at around 7 K. The preliminary estimated total heat dissipation of the holder is 2.39 ± 0.09 mW when we activated it for 532 s.
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