dataesr/scientific-paragraphs-categorization huggingface dataset:
We plan to employ 5-layer sapphire plates, which achieves an averaged modulation efficiency of about 92 % and 96 % for the 40-and 140-GHz LFT bands, respectively, and above 98 % for other frequency bands, as well as nulling the frequency-dependent fast-axis variation over the LFT bandwidth  [191] [192] [193]. The multi-layer sapphires will be glued by using a sodium silicate solution. The first preliminary tests with a polished 4 mm × 4 mm surface show that the mechanical strength is > 20 MPa, which is sufficiently high to mechanically treat the multi-layer sapphire stack as one bulk sample under the launch impact  [194]. We also test if there is any effect to the millimeter-wave transmittance with this bonding 41/156 ORIGINAL UNEDITED MANUSCRIPT scheme using a sapphire sample with a diameter of 100 mm, and we did not find any effect within the noise level of the measurement, equal to 2 % of the signal.
Mid-and High-Frequency Telescopes 4. 3. 1. Overview. The optimization of the instrumental design over the mid-and highfrequency range of LiteBIRD, spanning from 89 GHz to 448 GHz, led to a design with two fully refractive telescopes, as shown in Fig. 15. The frequency bands of the MFT range from 89 to 224 GHz, and from 166 to 448 GHz for the HFT (see Ref. [197]  for more details). When considered together, the two telescopes are referred to as the Mid-and High-Frequency Telescopes (MHFT). The choice to use two distinct fully refractive telescopes has been mainly driven by the constraints put on the HWP material and the anti-reflection coatings (ARCs), imposed by the broad frequency coverage and the limited mass budget and volume allocation. Each telescope features its own polarization modulator, in order to mitigate the bandwidth limitations of ORIGINAL UNEDITED MANUSCRIPT Fig.
ORIGINAL UNEDITED MANUSCRIPT the HWP mesh technology. The global design specifications of the MFT and HFT are summarized in Table  5. This design benefits from the broad expertise gained on many current and upcoming sub-orbital CMB experiments, such as BICEP/Keck  [198] , SPIDER  [199] , LSPE  [200] , and Simons Observatory  [201]. With these very compact on-axis designs, the MFT and HFT match the volume and weight constraints, mitigate straylight issues, and split the entire frequency range into two bands. This choice also offers more flexibility for an optimal design of the separate filtering chains. Dealing with two smaller compact telescopes will considerably simplify the assembly, integration, and testing (AIT) and assembly, integration, and verification (AIV) phases of the project and the ground calibration activities.
ORIGINAL UNEDITED MANUSCRIPT It will be essential to understand the higher-order optical coupling effects arising from a broad set of non-idealities, like imperfect dielectric-to-vacuum matching at the optical interfaces, imperfectly-absorbing tube surfaces and focal planes, scattering off internal surfaces, and thermal radiation pickup from the payload environment. Half-wave Plate. While the electromagnetic behavior of the mesh HWP is very well modeled and validated at the subsystem level, the presence of a mesh HWP along the optical path to the focal plane makes it necessary to model the whole system with accuracies beyond what is achievable with currently available simulation software. The need to capture the impact of imperfect and frequency-dependent phase shifts, and the effect of non-normal incidence on the final performance of the device creates a extremely complex modeling effort.
ORIGINAL UNEDITED MANUSCRIPT resulting artifacts in the reconstructed image at scales of a few degrees on the sky (see Fig. 17 ). Fig. 17 : Left: Example of optical ghosting at 90 GHz, from the combined effect of a non-ideal ARC, (in this case a single-layer ARC optimized for 150 GHz,) on MFT lenses and imperfect absorption on the focal plane, as seen in the telescope far field. A secondary beam-like feature can be shown out of the main beam pattern in this example. Right: Corresponding power distribution in the plane of the telescope, as predicted by these simulations.
ORIGINAL UNEDITED MANUSCRIPT The rotation is driven by an electromagnetic motor, based on the interaction between eight small cylindrical SmCo magnets placed on the edge of the rotor and 64 high purity copper coils placed on the stator. The motor magnets and the hysteresis in the main magnet assembly are the main contributions to the power load on the 5-K stage and must be minimized as much as possible. In addition, the eddy currents induced by the motor coils heat up the rotor, which can be cooled down only by radiation, a process that is not very efficient at cryogenic temperatures. The total heat load expected from both mechanisms is 2. 8 mW, which is within the requirement, with a 40 % margin. The rotor temperature is monitored by capacitive sensors  [213]  (3 % accuracy), which are also used to monitor the levitation height and the wobble of the rotor (10 µm resolution).
A thermal model built by Comsol Multiphysics 7 shows that after a slow rise the equilibrium temperature should be approximately 16 K for both modulators, assuming HWP emissivities ORIGINAL UNEDITED MANUSCRIPT of 0. 02 and 0. 03 for MFT and HFT, respectively, while the assumed emissivity of aluminum is 0. 5, achievable with a blackened surface  [214]. The position readout system uses an optical encoder, with 64 precision slits in the rotor ring periphery. The light from a warm temperature modulated LED is transferred to the rotor via an optical fiber, and the light transmitted through the slits is transferred back to a warm temperature detector via another optical fiber. This configuration minimizes the heat load on the different stages of the cryogenic system  [215]. The expected angular encoding accuracy is better than 0.
ORIGINAL UNEDITED MANUSCRIPT   it is wire-bonded to a flexible circuit leading to the cold readout. An overview of the two detector architectures is given in Fig. 22. The TES technology is able to reach the instantaneous sensitivity required by the LiteBIRD mission and is a mature design technology for ground-based and sub-orbital CMB experiments heritage  [220]. A demonstation of the noise equivalent power of a prototype AlMn TES bolometer operated at 100 mK is shown in Fig. 23. The readout used for these measurements utilizes an older digital frequency-domain multiplexing (DfMux) system with SQUIDs at 4. 8 K. Cosmic-ray mitigation is integrated directly into the focal-plane design to limit cosmic-ray impacts on low-ℓ systematics and data loss, described in detail in Sect. 5. 3. 4. The transient energy deposition of cosmic rays interacting with the spacecraft can create glitches in the timestream of data sent to the readout system.
ORIGINAL UNEDITED MANUSCRIPT The overall white noise requirement of the readout system is that it should increase the fundamental statistical noise already in the detection chain by no more than 10 % in each band, including yield-reduction due to the readout. Other requirements are that the readout-induced crosstalk be lower than 0. 3 % for every bolometer, and that ambient variable magnetic fields i n t he s pacecraft n ot s ignificantly in crease th e no ise in th e detection chain. 4. 5. 1. Cold Readout. The LiteBIRD readout system is improved compared to previously fielded DfMux systems by making some modifications to the cold circuitry. The previous resistive bias element at 4K has been changed to an inductor on the 100-mK stage and the SAA has also been moved onto the 100-mK stage  9.
Further refinement in the per-component noise injection allocation, given circuit component optimizations, are ORIGINAL UNEDITED MANUSCRIPT underway. Magnetic shielding of the SAAs is accomplished, as in other DfMux systems, with a hybrid system of niobium foil beneath the SAA to pin magnetic fields when in the superconducting state, and a µ-metal shield around the SAA to reduce field amplitude. ORIGINAL UNEDITED MANUSCRIPT 4. 5. 2. Warm Readout. The LiteBIRD warm electronics (WE) implement the noncryogenic portion of the DfMux hardware. This is divided into three separate electronics assemblies, as follows. • The signal-processing assembly (SPA) contains the field-programmable gate array (FPGA) that performs the digital signal processing and communication. Each SPA supports up to 15 multiplexing modules using four digitizer assemblies.
ORIGINAL UNEDITED MANUSCRIPT On the other hand, the 0. 1-K and 0. 35-K ADRs drivers of the cooling chain, responsible for driving the ADRs for the 0. 1-K and 0. 35-K stages, respectively, are connected to the MDPU-MH. The MDPU-L addresses the higher-temperature stages of the cooling chain, i. e. , the 2-K JT and 4-K JT drivers (JTD), the 15-K Pulse Tube cooler driver, and the pre-cooler driver (PCD). The two JTDs, responsible for driving the Joule-Thomson cryocoolers for the 1. 75-K and 4. 8-K stages, provide the AC power for the 3He JT and 4He JT mechanical coolers, respectively, monitor the temperatures that are provided, and monitor pressures and controlling valves in the JT circuits. The PCD, which is the cooler driver for the Stirling coolers used for the shield and JT pre-cooling, provides AC power for the Stirling mechanical coolers and monitors the temperatures that they are cooling.
Sub-kelvin Cooler. The sub-K cooler is provided by French Alternative Energies and Atomic Energy Commission (CEA). It works from 1. 75 K to 0. 1 K, as schematically shown in Fig. 29  and has been described in Ref. [240]. The 350-mK continuous cooling stage is obtained thanks to two ADR stages. Similarly, the 100-mK stage is obtained with two 60/156 ORIGINAL UNEDITED MANUSCRIPT additional ADR stages. For low temperatures, continuous cooling is achieved using a series configuration, with one stage being at a stable temperature, while a second stage is used to extract heat from the low temperature and dump it to the highest temperature interface.
61/156 ORIGINAL UNEDITED MANUSCRIPT Fig. 30 : Global calibration strategy. The colors of the circles give an indication of the accuracy foreseen for the related calibration operation (white indicates preliminary characterization, light blue is for verification, and dark blue identifies the phase for which the calibration will be ultimately performed). The flight calibration phase can be sub-divided into three categories: the calibration and performance verification phase prior to nominal observations; and calibration during and after the nominal observations. These are not detailed here.
Prospects for Ground Calibration. As discussed above, Fig. 31  illustrates the main steps that are foreseen today for beam characterization. To meet these requirements, the plan is to rely on a very tight connection between measurements performed both at warm and cold temperatures, together with the development of accurate software tools for instrumental modeling. • In the first phase, the plans are to go through characterizations of sub-systems (and combinations of components) at warm and cold temperature to consolidate the design 62/156 ORIGINAL UNEDITED MANUSCRIPT.
ORIGINAL UNEDITED MANUSCRIPT of the instrument as well as its optical modeling, allowing us to build the transfer function between warm and cold temperatures. The MHFT BBM is an example of activities in this phase of the development plan, with comparable activities being planned for LFT. The purpose of the BBM measurement campaign is to challenge the optical modeling of the MHFT refractive designs, to assess the achievable accuracy both for the modeling and for the radio-frequency (RF) measurements, to prepare the setups that will be used for the cold measurements, and to study various effects such as, for example, misalignment of components (tolerance analysis), standing waves, and ghosting. The BBM test plan foresees the following two models. (1) BBM-1 (corrugated horn with one lens): simulation and characterization at MFT and HFT frequencies in different labs with a reference common channel as a crosscheck.
ORIGINAL UNEDITED MANUSCRIPT we can assume that a planet, given its limited angular size with respect to the FWHM of LiteBIRD's beams and its considerable brightness, 10  can be considered as a bright point source that "samples" the radiation pattern γ(r). With these assumptions, one can estimate the value of γ(r) using γ(r) ∝ ∆T pl (r) T B,pl Ω b Ω pl. ( 21 ) Here ∆T pl represents the component of the signal that is caused by the presence of the planet along direction r, Ω b = 4π γ(r) dΩ is the angular beam size, Ω pl is the solid angle subtended by the planet, and T B,pl is the brightness temperature of the planet in the frequency band sampled by the detector. We have used Eq. (  21 ) to simulate how accurately we can expect to reconstruct the shape of γ, assuming that the radiation pattern has a perfectly symmetric Gaussian profile.
ORIGINAL UNEDITED MANUSCRIPT Note that the estimation here only relies on a single source, Jupiter, and thus concatinating other planets in future analyses should give a modest improvement in the statistical error. Should the error be too large, we will consider the possibility to run dedicated observations of planets to increase the integration time. To complete this picture, a preliminary estimation using data from Planck of the additionnel optical loading from head-on observations of Jupiter is approximately 1 % at 40 GHz, 10 % at 140 GHz, and 80 % at 337 GHz of the expected optical loading per band. The global impact of the detector non-linearities and saturation is under study. For the sidelobes, cross-checks between in-flight data, simulations, and ground-based characterization are foreseen.
Requirements. Bandpass frequency-resolution requirements have been studied in Ref. [246] , where an ideal rotating HWP has been assumed. The requirements are driven by the color-correction  [247]  uncertainty, that results from the calibration of the foreground signal when the CMB dipole is assumed as the photometric calibrator. With decreasing frequency-resolution of the bandpass response, the color-correction uncertainty increases. This appears clear from the expression for the color-correction factor γ: γ d,s =    dν G(ν) Id,s(ν) Id,s(ν0) dν G(ν) ∂B(ν,T ) ∂T T0    ∂B(ν 0 , T ) ∂T T0 , (22) where the indices "d" and "s" refer, respectively, to dust and synchrotron, G(ν) is the band-pass function, I d (ν) (I s (ν)) is the dust (synchrotron) spectrum, ν 0 is the effective 67/156 ORIGINAL UNEDITED MANUSCRIPT central frequency of the given band, B(ν, T ) is the blackbody spectrum, and T 0 is the CMB temperature.
ORIGINAL UNEDITED MANUSCRIPT measurements to gain S/N against having a higher spectral resolution knowledge used in the removal of specific spectral features (such as CO). The strategy for LiteBIRD is slightly different. At the component level, the spectral response characterization is planned to be performed using a vector network analyzer (VNA) with extremely high spectral resolution in order to characterize the potential presence of inherent fringes. At the instrument level, spectral measurements are part of the datacube reconstruction (cf. Sect. 4. 8. 4), which should allow us to achieve the required sub-GHz resolution. In addition, the out-of-band rejection (particularly important for component separation), which could be characterized down to levels of 10 -12 , as was done for the Planck -HFI filter chains  [248] , will be reconstructed using a combination of component-level and end-to-end cryogenic tests.
ORIGINAL UNEDITED MANUSCRIPT The requirements on the absolute angle consist of a global offset, which accounts for the mismatch between the SVM and the PLM, and three additional ones that account for the mismatch between the PLM and each of the three focal planes. The following cases have been considered: • Case 0, no correlations; • Case 1, the four offsets are fully correlated; • Case 2, the global offset is uncorrelated with any of the three focal plane offsets, and the latter ones are fully correlated. The corresponding requirements are given in Fig. 35  (right panel). They appear less stringent for the high frequency channels, as opposed to the case of most of the other systematics effects, like, for instance, the beam knowledge requirements, which is more stringent at high frequnecy mainly because of the effect of the higher resolution in these bands.
ORIGINAL UNEDITED MANUSCRIPT showed that the offset angles could be recovered by imposing the null detection of C EB ℓ , using two different analyses. This way of calibrating angles, called "self-calibration"  [255] , eliminates LiteBIRD's ability to probe new parity-violating physics using the cosmological EB correlation. The potential presence of the EB correlation intrinsic to the Galactic foreground emission, which is yet to be found  [53, 72, 256, 257] , could complicate the analysis further. The method of Ref. [251]  can mitigate these complications, restoring LiteBIRD's ability to probe new physics and account for possible foreground EB signals (see Sect. 6. 2). Prospects for In-flight Calibration using the Crab Nebula. The Crab Nebula (Tau A) is one of the brightest compact sources in the sky in the microwave range, and the brightest one in polarization.
7 arcmin pixel in the Stokes Q and U maps, and computing the measured angle obtained by convolution of the Q and U maps with the LiteBIRD beams. Repeating the process 10,000 times we find that the standard deviation of the distribution of measured angles is smaller than the required 3 arcmin if the noise per pixel in the reference Stokes parameter maps is below about 30 µK rms at 100 GHz, and 10 µK rms at 337 GHz. These stringent reqruiements motivate us to explore further detailed 72/156 ORIGINAL UNEDITED MANUSCRIPT measurements of the Crab using forthcoming surveys in order to have the reference maps ready at the time of the LiteBIRD mission. Prospects for Ground Calibration.
ORIGINAL UNEDITED MANUSCRIPT As shown in Fig. 30 , the general plan is to characterize the relative polarization angles per focal plane during the end-to-end (E2E) cryogenic operations at the telescope level. Special care will be taken to define a common reference frame or reference transposition from sub-system characteristics to the telescopes, up to the PLM-SVM-integrated instrument. For reference, the end-to-end ground calibration test campaign for Planck -HFI ultimately achieved an average of 1. 5 • accuracy while the sub-system level (i. e. , single cooled pixel) testing had achieved an average accuracy of 0. 1 •  [270, 271]. For LiteBIRD since we are using both an HWP and sinuous antenna  [272] , the bandpasses and the polarization angle are therefore highly coupled. It is possible to test for the overall spectral efficiency of a channel with an unpolarized source, and it is possible to accurately measure the maximum efficiency angle of a given detector, but for an end-to-end test of the whole instrument, the two effects are combined in a non-trivial way.
ORIGINAL UNEDITED MANUSCRIPT VNA or other coherent source) and to measure spectra at each small variation of HWP angle position in order to be able to reconstruct the expected modulation curve for any given spectral index source. The end-to-end calibration operations are complementary to the RF test campaign (cf. Sect. 4. 8. 2), which will specifically address the impact of the optical distortion and coating inefficiencies. A measurement campaign has already been performed on the LFT small-scale model and is reported in Ref. [175]. In addition, various instrumental parameters may also impact the polarization angle and will be characterized at the component level to check their accuracy with respect to the requirements flowdown, in particular on the knowledge of the encoding angle HWP PMU (cf.
ORIGINAL UNEDITED MANUSCRIPT of the instrumental design. This section gives an overview of the main parameters entering the IMo. Table  12  gives the values of the main baseline parameters common to the three telescopes, LFT, MFT, and HFT. The parameters related to the observational scan strategy are further defined by the schematics shown in Fig. 37. The duration of the mission is assumed to be three years throughout this section, except where explicitly stated otherwise. We optimize the scan strategy parameters including α, β, and the spin rate so as to have the distributions as uniform as possible for the hits over the entire sky area and for the scanning directions in inidividual sky pixels. A spin rate less than 0. 05 rpm is found to give non-uniform distributions for both quantities.
ORIGINAL UNEDITED MANUSCRIPT optics simulations similar to those described in Ref. [277] ), and number of detectors. The details of the sensitivity calculations are given in Sect. 5. 1. By default the bandpasses are assumed to be tophat functions whose bandwidths are given in the same table. Table  13 : LiteBIRD sensitivities. We show values related to the sensitivity in 15 observational bands. From left to right the columns are: the telescope covering the band (or "comb. " for combined values); the band identification number; the band center frequency in GHz; the bandwidth in GHz and its ratio to the center frequency; the main beam size FWHM in arcmin; the total number of detectors; the array NET in µK √ s; and the sensitivity in µKarcmin. The two values of the beam size and the sensitivity for the LFT 68-, 78-, and 89-GHz bands in parentheses are for the two detector pixel sizes of 16 and 32 mm.
ORIGINAL UNEDITED MANUSCRIPT The noise-equivalent power (NEP) of each detector is predicted from a quadrature sum of the expected photon noise (NEP ph ), thermal carrier noise of the bolometer (NEP th ), readout noise (NEP read ), and extra noise (NEP ext ) sourced from the environment and unknowns. The NEP of a single detector (NEP det ) may therefore be expressed as NEP det = NEP 2 ph + NEP 2 th + NEP 2 read + NEP 2 ext , (27) where all the components are assumed to be mutually uncorrelated. The quantity NEP ph is deduced from the expected loading on the detectors (taking account of the various optical elements, their intrinsic characteristics, and the temperature to which they are cooled), while NEP th is derived from the temperature of the bath and the expected critical temperature of the bolometers.
ORIGINAL UNEDITED MANUSCRIPT Galactic foregrounds, are in thermodynamical CMB temperature units, µK CMB. The CMB angular power spectra correspond to the Planck 2018 best-fit parameters  [279] , with the six ΛCDM parameters corresponding to {H 0 , Ω b h 2 , Ω c h 2 , τ, n s , A s } = {67. 36 km s -1 Mpc -1 , 0. 02237, 0. 12, 0. 0544, 0. 965, 2. 099 × 10 -9 }, with lensing and with no tensors, i. e. , r = 0. Diffuse foregrounds are produced with the public package Python Sky Model (PySM) with default implementation of the amplitude of foregrounds, and spatially varying spectral indices  [280, 281] , corresponding to the d1s1 parametrization in PySM. The Galactic polarized emission is composed of thermal dust and synchrotron models, dominating the polarization emission at frequencies higher and lower than about 70 GHz, respectively  [282].
ORIGINAL UNEDITED MANUSCRIPT component separation. All templates are convolved with top-hat bandpasses (see Table  13  for the band centers and widths) and co-added to form input sky maps. Concerning beam convolution, two series of maps are produced, for comparison purposes. The first one is a direct convolution with a Gaussian circular beam shape with FWHMs from the IMo. The second one is a timeline-based series of simulations, generated with the public package Time-Ordered Astrophysics Scalable Tools (TOAST)  14. The convolution of the signal with the beam simulated in GRASP (encoding for the whole 4π beam pattern) is performed with the libconviqt 15  library, implementing beam convolution on a sphere based on Ref. [285]. For the first set of simulations, the noise was added to the co-added multi-frequency and multi-component maps for the Gaussian circular beam convolutions.