LFI design, qualification, and performance

Overview

The Planck-LFI instrument is an array of 11 radiometric receivers in the Ka, Q and V bands, with centre frequencies close to 30, 44 and 70 GHz. The exact centre frequencies for each receiver are reported in #planck2011-1-4 [[http://www.rssd.esa.int/doc_fetch.php?id=3135856&page=1 Planck early results.

The heart of the LFI instrument is a compact, multi-frequency array of differential receivers with ultra-low-noise amplifiers based on cryogenic indium phosphide (InP) high-electron-mobility transistors (HEMTs). To minimise power dissipation in the focal plane unit, which is cooled to 20 K, the radiometers are split into two subassemblies connected by a set of waveguides, as shown in figure 1, left panel.

Figure 1. Left Panel: the LFI instrument with main thermal stages, focal plane, waveguides and sorption cooler piping highlighted. Right Panel: Labelling of feed horns on the LFI focal plane.

The LFI horns are situated in a ring around the HFI, see figure 1 – right panel. Each horn collects radiation from the telescope and feeds it to one or more detectors. The radiometer design is driven by the need to suppress 1/f-type noise induced by gain and noise temperature fluctuations in the amplifiers, which would be unacceptably high for a simple total power system. A differential pseudo-correlation scheme is adopted, in which signals from the sky and from a black-body reference load are combined by a hybrid coupler, amplified in two independent amplifier chains, and separated out by a second hybrid (figure 2). The sky and the reference load power can then be measured and differenced. Since the reference signal has been subject to the same gain variations in the two amplifier chains as the sky signal, the true sky power can be recovered. Insensitivity to fluctuations in the back-end amplifiers and detectors is realized by switching phase shifters at ∼8 kHz synchronously in each amplifier chain. The rejection of 1/f noise as well as the immunity to other systematic effects is optimised if the two input signals are nearly equal. For this reason the reference loads are cooled to ∼4 K by mounting them on the 4-K structure of the HFI. In addition, the effect of the residual offset (< 2 K in nominal conditions) is reduced by introducing a gain modulation factor in the on-board processing to balance the output signal (#Seiffert2002). The differencing receiver greatly improves the stability of the measured signal.

Figure 2. Schematic of the LFI front-end radiometer. The front-end unit is located at the focus of the Planck telescope, and comprises: dual profiled corrugated feed horns; low-loss (∼0.2 dB), wide-band (> 20%) ortho-mode transducers; and radiometer front-end modules with hybrids, cryogenic low noise amplifiers, and phase switches.

First assessment of the Low Frequency Instrument in-flight performance]]; for simplicity, here we will refer to the three channels using their nominal centre frequency. A detailed description of the LFI instrument is given in #bersanelli2010 [Planck pre-launch status: Design and description of the Low Frequency Instrument], and references therein.

The LFI description

The LFI instrument (see figure 1 above) consists of a 20 K focal plane unit hosting the corrugated feed horns, the orthomode transducers (OMTs) and the receiver front-end modules (FEMs). Forty four composite waveguides #darcangelo2009a are interfaced with three conical thermal shields and connect the front-end modules to the warm (~300 K) back-end unit (BEU) containing a further radio frequency amplification stage, detector diodes and all the electronics for data acquisition and bias supply.

Best LFI noise performance is obtained with receivers based on InP High Electron Mobility Transistor (HEMT) low noise amplifiers (LNAs) for minimal power dissipation and best performance. To further minimise power consumption in the focal plane, the radiometers are split into two sub-assemblies connected by waveguides, one located at the telescope focal area, the other on the 300 K portion of the Planck satellite. These design features allow the entire front-end LNAs dissipation to be <0.55 W, which enables the active cooling of the focal assembly. This is achieved with a vibration-less hydrogen sorption cooler, which also provides 18 K pre-cooling to the HFI helium J-T cooler. Two sorption cooler units are included in the flight hardware.

As shown schematically in Figure 3 below, the LFI consists of the following subsystems:

• Radiometer Array Assembly (RAA)
• Sorption Cooler Subsystem (SCS)
• Radiometer Electronics Box Assembly (REBA)

The RAA includes the Front End Unit (FEU) and the Back End Unit (BEU), connected via waveguides. The FEU is located at the focus of the telescope, as one component of the joint LFI/HFI focal assembly (see sections below). The BEU is mounted on the top of the Planck service module (SVM). The REBA (Radiometer Electronics Box Assembly) and the warm parts of the Sorption Cooler System (SCS) are located on one of the lateral panels of the SVM. The FEU and the Sorption Cooler Compressor (SCC) are connected by concentric stainless steel tubes. The smaller tube carries hydrogen at ∼60 atmospheres from the cooler compressors to the FEU, while the larger tube returns the hydrogen at ∼0.3 atmospheres. These units are described in following sections and in the LFI Appendix, the SCS is described in details in the Sorption Cooler section. All LFI units are linked together by the LFI harness, which also connects to the spacecraft interface.

Figure 3. Block Diagram of LFI

Radiometer Array Assembly (RAA)

The Radiometer Array Assembly (RAA) consists of two main units (the front end unit, FPU and the Back End Unit, BEU), connected by a set of waveguides. The Focal Plane Unit (FPU) is the heart of the LFI instrument and it contains the feed array and associated orthomode transducers (OMTs) and FEMs, all cooled to 20 K by the sorption cooler. The FPU comprises a set of 11 modules, which are mounted on a mechanical support which meets the thermo-mechanical requirements of the instrument and adds thermal inertia. The BEU comprises the radiometer Back End Modules (BEM) and the Data Acquisition Electronics (DAE), which are connected by an internal harness. The HFI Unit is located inside the LFI FPU and supported by the LFI structure. The LFI structure gives the mechanical and thermal interface to the HFI unit with the proper stiffness and thermal de-coupling. The LFI structure also guarantees the proper alignment of the HFI detector with the telescope focal plane.

The time scale of the stability of the receiver is driven by the 1 rpm rotation speed of the spacecraft, which requires a very low 1/f-noise or gain variation of the low noise amplifiers and other components. The LFI uses a pseudo-correlation receiver concept (Figure 4 below). This radiometer concept is chosen to maximise the stability of the instrument by reducing the effect of non-white noise generated in the radiometer itself. In this scheme, the difference between the inputs to each of the chains (the signal from the telescope and that from a reference black body respectively) is continuously being observed. To remove the effect of instability in the back-end amplifiers and detector diodes, it is necessary to switch the signal detected at the diodes at high rate. The signals from the sky and from a reference load are combined by a hybrid coupler, amplified in two independent amplifier chains, and separated out by another hybrid. The sky and the reference load power can then be measured and differenced. Since the reference signal has been subject to the same gain variations in the two amplifier chains as the sky signal, the true sky power can be recovered. The differencing receiver greatly improves the stability if the two input signals are almost equal, at a cost of a factor of [math]\sqrt 2 \; [/math] in sensitivity compared to a perfectly stable total-power radiometer with the same noise temperature and bandwidth. This radiometer concept is capable of greatly reducing the knee frequency. We define as Radiometer Chain Assembly (RCA, see Figure 4) each functional unit from the feed horn to the BEM. The RAA therefore includes a set of 11 RCAs and the Data Acquisition Electronics, all mounted on a suitable mechanical structure (see also Figure 3 above). Although there are differences in the details of the radiometer chains at different frequencies, their overall configuration is similar, and a general description of its design is provided in this section. Planck LFI has 11 Radiometer Chain Assembly (RCA). Each RCA is constituted by feed horn and FEM in the FEU (at 20 K), BEM (at 300 K) in the BEU and four waveguides that connect each FEM-BEM couple. The frequency distribution of the RCA is the following:

• 2 RCAs at 30 GHz;
• 3 RCAs at 44 GHz;
• 6 RCAs at 70 GHz.

Figure 4. A complete RCA from feed-horn to analog voltage output. The insets show the OMT, the details of the 20 K pseudo-correlator and of the back-end radio-frequency amplification, low-pass filtering, detection and DC amplification.

Radiometer Chain Assembly (RCA)

Every RCA consists of two radiometers, each feeding two diode detectors (see Figure 3 above), for a total of 44 detectors. The 11 RCAs are labelled by a numbers from 18 to 28 as outlined in Figure 1, right panel.

Figure 3 provides a more detailed description of each radiometric receiver. In each RCA, the two perpendicular linear polarisation components split by the OMT propagate through two independent pseudo-correlation differential radiometers, labelled as M or S depending on the arm of the OMT they are connected to (Main or Side, see lower-left inset of Figure 3).

In each radiometer the sky signal coming from the OMT output is continuously compared with a stable 4 K blackbody reference load mounted on the external shield of the HFI 4 K box #valenziano2009. After being summed by a first hybrid coupler, the two signals are amplified by ~30 dB, see upper-left inset of Figure 3. The amplifiers were selected for best operation at low drain voltages and for gain and phase match between paired radiometer legs, which is crucial for good balance. Each amplifier is labelled with codes 1, 2 so that the four outputs of the LNAs can be named with the sequence: M1, M2 (radiometer M) and S1, S2 (radiometer S). Tight mass and power constraints called for a simple design of the Data Acquisition Electronics (DAE) box so that power bias lines were divided into five common-grounded power groups with no bias voltage readouts; only the total drain current flowing through the front-end amplifiers is measured and is available to the house-keeping telemetry (this design has important implications for front-end bias tuning, which depends critically on the satellite electrical and thermal configuration and was repeated at all integration stages, during on-ground and in-flight satellite tests). A phase shift alternating between [math] 0^\circ \; [/math] and [math]180^\circ \; [/math] at the frequency of 4096 Hz is applied in one of the two amplification chains and then a second hybrid coupler separates back the sky and reference load components that are further amplified and detected in the warm BEU, with a voltage output ranging from -2.5 V to +2.5 V.

Each radiometer has two output diodes which are labelled with binary codes 00, 01 (radiometer M) and 10, 11 (radiometer S), so that the four outputs of each radiometric chain can be named with the sequence: M-00, M-01, S-10, S-11.

After detection, an analog circuit in the DAE box removes a programmable offset in order to obtain a nearly null DC output voltage and a programmable gain is applied to increase the signal dynamics and optimally exploit the ADC input range. After the ADC, data are digitally down-sampled, re-quantised and compressed in the REBA according to a scheme described in #herreros2009, maris2009, before preparing telemetry packets. On ground, telemetry packets are converted to sky and reference load time ordered data after calibrating the ADU samples into volt considering the applied offset and gain factors.

To first order, the mean differential power output for each of the four receiver diodes can be written as follows #seiffert2002, mennella2003, bersanelli2010 [Planck pre-launch status: Design and description of the Low Frequency Instrument]:

[math] \label{eq:power} P_{\rm out}^{\rm diode} = a\, G_{\rm tot}\,k\,\beta \left[ T_{\rm sky} + T_{\rm noise} - r\left( T_{\rm ref} + T_{\rm noise}\right) \right] [/math]

where [math]G_{\rm tot} \;[/math] is the total gain, [math]k \;[/math] is the Boltzmann constant, [math]\beta \;[/math] the receiver bandwidth and [math]a \;[/math] is the diode constant. [math]T_{\rm sky} \;[/math] and [math]T_{\rm ref}\; [/math] are the average sky and reference load antenna temperatures at the inputs of the first hybrid and [math]T_{\rm noise} \;[/math] is the receiver noise temperature.

The gain modulation factor #mennella2003, planck2011-1-6 [Planck early results. The Low Frequency Instrument data processing], [math]r[/math], is defined by:

[math] \label{eq:erre1} r = \frac{T_{\rm sky} + T_{\rm noise}}{T_{\rm ref} + T_{\rm noise}} [/math]

and is used to balance (in software) the temperature offset between the sky and reference load signals and minimise the residual 1/[math]f \;[/math] noise in the differential datastream. This parameter is calculated from the average uncalibrated total power data using the relationship:

[math] \label{eq:erre2} r = \langle V_{\rm sky} \rangle/ \langle V_{\rm ref}\rangle, [/math]

where [math]\lt V_{\rm sky}\gt \;[/math] and [math]\lt V_{\rm ref}\gt \;[/math] are the average sky and reference voltages calculated in a defined time range. The white noise spectral density at the output of each diode is essentially independent from the reference-load absolute temperature and is given by:

[math] \label{eq:dt1} \Delta T_0^{\rm diode} = \frac{2\,(T_{\rm sky}+T_{\rm noise})}{\sqrt{\beta}}. [/math]

If the front-end components are not perfectly balanced, then the separation of the sky and reference load signals after the second hybrid is not perfect and the outputs are mixed. First-order deviations in white noise sensitivity from the ideal behaviour are caused mainly by noise temperature and phase-switch amplitude mismatches. Following the notation used in #seiffert2002, we define [math]\epsilon_{Tn} \; [/math], the imbalance in front end noise temperature, and [math]\epsilon_{A1} \; [/math] and [math] \epsilon_{A2} \;[/math] , the imbalance in signal attenuation in the two states of the phase switch. Equation above for the two diodes of a slightly imbalanced radiometer then becomes

[math] \label{eq:dt2} (\Delta T^{diode} )^2 ≈ (\Delta T_0^{diode})^2 ( 1± \frac{\epsilon_{A1}- \epsilon_{A2}}{2} + \alpha \epsilon_{Tn}) [/math]

which is identical for the two diodes apart from the sign of the term [math](\epsilon_{A1} − \epsilon_{A2} )/2[/math], representing the phase switch amplitude imbalance. This indicates that the isolation loss caused by this imbalance generates an anti-correlation between the white noise levels of the single-diode data streams. For this reason, the LFI scientific data streams are obtained by averaging the voltage outputs from the two diodes in each radiometer:

[math] \label{eq:v1} V^{rad}_{out} = w_1 V^{diode\,1}_{out} +w_2 V^{diode\,2}_{out} [/math]

where [math]w_1 [/math] and [math]w_2[/math] are inverse-variance weights calculated from the data as discussed in #planck2011-1-6. This way, the diode-diode anti-correlation is cancelled, and the radiometer white noise becomes

[math] \label{eq:dt3} \Delta T^{rad} ≈ \frac{ T_0^{diode}}{\sqrt{2}} (1+\alpha \epsilon_{Tn})^{1/2} [/math]

In Equations above, [math]\epsilon ≪ 1[/math], while [math] \alpha [/math] is a term [math]\simeq 1 [/math] given by:

[math] \label{eq:alpha} \alpha = \frac{ T_{noise} (2 \; T_{noise} + T_{sky} + T_{ref} } {2 (T_{sky} + T_{noise} )(T_{ref} + T_{noise})} [/math]

See Diode Combination section for the details of the diode combination procedure.

In Figure 4 below we show a close-up of the two front end modules of an RCA with the four phase switches which are labelled with the four letters A and B (main arm), C and D (side arm). Each phase switch is characterised by two states: state 0 (no phase shift applied to the incoming wave) and state 1 ([math]180^\circ[/math] phase shift applied) and can either stay fixed in a state or switch at 4 kHz between the two states.

Phase switches are clocked and biased by the DAE and their configuration can be programmed via telecommand. In order to simplify the instrument electronics, phase switches are configured and operated in pairs: A/C and B/D. This means that if phase switches A and C are switching at 4 kHz then B and D are fixed both in the same state (either 0 or 1). This simplification, required during the design phase to comply with mass and power budgets, comes at the price of loosing some setup redundancy.

Figure 4. Close-up of the two front-end modules of an RCA. There are four phase switches, labelled A, B, C and D. Each switch can be fixed in one of its two positions (labelled as 0, 1) or switch at 4 kHz between 0 and 1. Phase switches are clocked and biased by the DAE in pairs: A/C and B/D.

Feed Horns (FH)

Dual profiled corrugated horns have been selected at all LFI frequencies as the best design in terms of shape of the main lobe, level of the side lobes, control of the phase centre, and compactness. Details of the design, flight model and tests of Planck-LFI feed horns can be found in #villa2009 and in the corresponding Appendix section.

OrthoMode Transducers (OMT)

The Ortho–Mode Transducer (OMTs) separates the radiation collected by the feed horn in two orthogonal polarisation components. It consists of a circular to square waveguide transition (directly connected to the FH), a square waveguide section and two separate rectangular waveguide (the through and side arms, which separate and pick up the orthogonal polarisation, connected with the FEU). On the side arms is always present a 90 degrees bend, while a twist is also necessary on the main (30 and 44 GHz) and side (70 GHz) arm, in order to math the FEU polarisation.

The details of the flight models and measurements of the Planck LFI ortho-mode transducers can be found in #darcangelo2009b and in the corresponding Appendix section.

Front End Modules (FEM)

Front End Modules are located in the FPU, just in cascade of the Feed Horn and the Ortho Mode Transducers. 70 GHz FEMs are mounted onto the inner wall of the mainframe (the wall facing HFI instrument) from the HFI side. 44 and 30 GHz FEMs are inserted into the mainframe from the WG side and fixed to the bottom plate. Screws to bottom plate are inserted from WG side. The LFI FEMs are the first active stage of amplification of the radiometer chain. Each FEM contains four amplification paths. Each path is composed by several cascaded LNAs followed by a phase switch. Two passive hybrids, at the input and output of the FEM, are used to mix couples of signals of the same radiometer (see Figure 4). This makes the instabilities of each chain to be applied to both the sky and load signals.

The passive hybrid coupler (magic-tee) combines the signals from the sky and cold load with a fixed phase offset of either 90 deg or 180 deg between them. It has a 20% bandwidth, low loss, and amplitude balance needed at the output to ensure adequate signal isolation.

The details of the design, development and verification of the 70 GHz front-end modules for the Planck Low Frequency Instrument can be found in #varis2009 and in the corresponding Appendix section.

Waveguides

The LFI Front End Unit (FEU) is connected to the Back End Unit (BEU) by 44 rectangular waveguides approximately 1.5-2.0 meter long. Each waveguide exhibits low voltage standing wave ratio, low thermal conductivity, low insertion loss, and low mass. In addition, the waveguide path shall permit the LFI/HFI integration and the electrical bonding between FPU and BEU. Because of the Focal Plane Unit arrangement, the waveguides are in general twisted and bended in different planes and with different angles, depending on the particular waveguide. From the thermal point of view the waveguides have to connect 2 systems (BEM and FEM) that are at very different temperatures. At BEM level the waveguides are at a temperature of 300K while at FEM level the temperature is 20K. The waveguides have to reduce the thermal flow from 300K to 20K. In Figure 1 (left panel) a conceptual sketch of the LFI configuration is shown.

Details of the Planck-LFI flight model of the composite waveguides can be found in #darcangelo2009a and in the corresponding Appendix section.

Back End Modules (BEM)

The BEMs are composed by four identical channels each made of Low Noise Amplifiers (LNA), RF Band Pass Filter, RF to DC diode detector and DC amplifiers. The FEM output signals are connected by waveguide from the Focal Plane Unit (FPU) assembly to the Back End Modules (BEM’s) housed adjacent to the Data Acquisition Electronics (DAE) assembly. To maintain compatibility with the FEM’s, each BEM accommodates four receiver channels from the four waveguide outputs of each FEM. The BEM internal signal routes are not cross coupled and can be regarded as four identical parallel circuits. Each BEM is constructed as two mirror halves. The two amplifier/detector assemblies each contain two amplifier/detector circuits. Each is supplied from one of a pair of printed circuit boards which also house two DC output amplifiers.

The details of the design, development and verification of the 30 and 44 GHz back-end modules for the Planck Low Frequency Instrument can be found in #artal2009. The details of the design, development and verification of the 70 GHz back-end modules for the Planck Low Frequency Instrument can be found in #varis2009. Details are reported also in the corresponding Appendix section.

4K Load

The purpose of the 4 K reference load is to provide the radiometer with a stable reference signal. Reducing the input offset (the radiometric temperature difference between the sky and the reference load) reduces the minimum achievable radiometer 1/f noise knee frequency for a given amplifier fluctuation spectrum. A reference load temperature that matches the sky temperature (approximately 2.7 K) would be ideal.

Details of the design, characteristics and performance of the LFI 4K reference load units are given in #valenziano2009 and in the corresponding section of the LFI Appendix.

LFI Naming Convention

The naming of all the LFI elements is described in the previous sections but here is summarized again for clarity.

The 11 RCAs are labelled by a numbers from 18 to 28 as outlined in Figure 1, right panel. In each RCA, the two perpendicular linear polarisation components are labelled as M or S according to the arm of the OMT they are connected to (Main or Side, see lower-left inset of Figure 3).

Each front-end amplifier (see upper-left inset of Figure 3) is labelled with codes 1, 2 so that the four outputs of the FEM LNAs can be named with the sequence: M1, M2 (radiometer M) and S1, S2 (radiometer S).

Each radiometer has two output diodes (see upper-right inset of Figure 3) which are labelled with binary codes 00, 01 (radiometer M) and 10, 11 (radiometer S), so that the four outputs of each radiometric chain can be named with the sequence: M-00, M-01, S-10, S-11.

REBA

The Radiometer Electronics Box Assembly (REBA) is the electronic box in charge of processing the digitized scientific data and to manage the overall instrument. It is also in charge of the communication with the spacecraft. There are two REBA boxes, one nominal and one redundant. The redundancy concept is cold, which means that both boxes are never ON at the same time; the operation of each unit shall be managed by the spacecraft switching-on the corresponding unit. The REBA ASW (Application SoftWare) is the same in each REBA box.

Each REBA consists of the following subunits:

• The Power Supply Unit (PSU) which feeds the REBA unit. It consists of a DC/DC converter that converts the primary power received from the spacecraft PDU to the secondary regulated voltages required only by the REBA and provides galvanic isolation towards the spacecraft side of the interface. The PSU DC/DC converter also receives the On-Board Clock (OBC) from the CDMS that is used to increment the internal On Board Time register. There is no software interface with the REBA ASW.
• The Data Acquisition Unit (DAU) performs the analogue to digital conversion of the analogue housekeeping data of the REBA itself (temperatures and voltages). The REBA ASW collects from the DAU the HK data.
• The Signal Processing Unit (SPU) is a computing subunit in charge of the reduction and compression of the science data and implements part of the REBA ASW, the SPU ASW (stored in the EEPROM located in the DPU board and transferred to the SPU by the DPU ASW). It receives the science data from the DAE through a IEEE 1355 link implemented in a SMCS chip. A second IEEE 1355 link is used to control by link the remote DAE SMCS chip. The third IEEE 1355 link communicates with the DPU. A “Data Ready” electrical signal is connected between DAE and the SPU, this signal produces an interruption in the SPU when the DAE is ready to transfer data.
• The Digital Processing Unit (DPU) is a computing subunit and implements part of the REBA ASW, the DPU ASW. The DPU is in charge of the control and monitoring of the instrument as well as the communication with the spacecraft (CDMS). It contains another SMCS chip with 3 IEEE 1355 links that communicate with the SPU, and the DAE. A MIL-STD 1553B link is used to communicate with the CDMS. One IEEE 1355 link is used by the DPU ASW to communicate with the DAE to control by link the SMCS chip of DAE, the second one is used to communicate with the DAE to transfer commands and HK and the third one is used by DPU ASW to communicate with the SPU (commands and TM). Two Reset electrical lines are provided by the DPU to reset each of the two SMCS chips of DAE. The DPU ASW is stored in the EEPROM.

A detailed description of the Planck LFI REBA can be found in #herreros2009.

Instrument On-board Software

The REBA software is the on board software of LFI. It is installed in the two computing subunits of REBA: the DPU, responsible of the control and monitoring of the instrument and the interface with the spacecraft and; the SPU, responsible of the data reduction and compression. The REBA software can be classified (see Figure 6) into:

1. the REBA Start-up Software (SUSW), installed in the PROM memories, which is the bootstrap code to switch on both the subunits;

2. the Application Software (ASW), which performs the nominal operations of the REBA;

3. the REBA Low Level Software Drivers (LLSWDRV) which are functions provided to the ASW to access the hardware capabilities.

Figure 6. REBA Software, high level product tree

The SPU SUSW and DPU SUSW, located in the PROM memories of SPU and DPU, respectively, are in charge of the booting of the subunits.

The REBA ASW performs the following main functions:

• SPU ASW reduction and compression of the scientific data;
• DPU ASW: control and monitoring of the instrument, interface with the spacecraft to transfer data and receive commands to/from ground, communication with the SPU SUSW during the start-up procedure to load the SPU ASW.

The REBA ASW checks periodically the following parameters:

− Science TM rate produced on board in order to control the filling of the spacecraft mass memory;

− CPU load of the SPU;

− Focal Plane temperature sensors;

− The communication links between REBA and DAE.

In case of deviations from nominal values, the REBA ASW activates autonomy functions that put the instrument in a safe state or recover from non-nominal situations. Autonomy functions allows to:

- Re-enable, in some cases, previously disabled science processing;

- Switch-off the Front End Unit by sending Disable RCA DC/DC commands to the DAE;

- Try to resume the communication between REBA and DAE or ask the CDMS to switch off the RAA.

The DPU ASW reports the activation of any autonomous function by sending to the CDMS an event report. The REBA monitors some LFI HK parameters in order to manage to some extent the safety of the instrument.

Reduction and Compression of Science Data

To asses stability against 1/f noise, the Low Frequency Instrument (LFI) on-board the Planck mission will acquire data at a rate much higher than the data rate allowed by the science telemetry bandwidth of 35.5 kbps. The data are processed by an on-board pipeline, followed on-ground by a decoding and reconstruction step, to reduce the volume of data to a level compatible with the bandwidth while minimizing the loss of information. The on-board processing of the scientific data used by Planck/LFI to fit the allowed data-rate is an intrinsically lossy process which distorts the signal in a manner which depends on a set of five free parameters ([math] N_{aver}, r_1, r_2, q, O \,[/math]) for each of the 44 LFI detectors. Here we briefly describe the characteristics of this algorithm and the level of distortion introduced by the on-board processing as a function of these parameters. A full description of the Planck LFI on-board data handling system and the tuning and optimization method of the on-board processing chain can be found in #maris2009.

The strategy adopted to fit into the bandwidth relies on three on-board processing steps: downsampling, pre-processing the data to ensure loss-less compression, and loss-less compression itself. To demonstrate these steps, a model of the input signal shall be used. It has to be noted that while the compression is loss-less, the pre-processing is not, due to the need to rescale the data and convert them in integers, (a process named data re-quantizzation). However, the whole strategy is designed to asses a strict control of the way in which lossy operations are done, of the amount of information loss in order to asses optimal compression rate with minimal information loss.

A schematic representation of the sequence in which these steps are applied on-board and whenever possible reversed on-ground is given in figure 7 below.

Figure 7. Schematic representation of the scientific onboard and ground processing for the Planck/LFI. Cyan boxes represent REBA operations, yellow boxes ground operations. Green pads specify the parameters needed by each operation. TOI could be produced both in undifferentiated form ([math] T_{sky}, \, T_{load} \, [/math] stored separately) or in differentiated form.

The figure refers to a single radiometer chain and is ideally splitted into two parts: the upper part depicts the on-board processing with cyan boxes denoting the main steps. The corresponding on-ground processing is depicted in the lower part with the main steps colored in yellow. Green pads represents the processing parameters. The first four of them are referred to as REBA parameters, and they are applied both on-board and on-ground. The parameters are: the number of ADC raw samples to be coadded to form an instrumental sample, [math]N_{aver}[/math], the two mixing parameters [math]r_1, r_2 [/math], the offset [math] O[/math] to be added to data after mixing and prior to re-quantization, and the re-quantization step [math]q[/math]. It is important to note that the on-board parameters are set by telecommands and are stamped in each scientific packet. The gain modulation factor, [math]r[/math] (see Eq. \ref{eq:erre1} in RCA section above), is a parameter of the ground processing and is computed from the total power data received on ground. The final products in the form of Time Ordered Data (TOI) either in total power or differentiated are stored in an archive represented by the light-blue cylinder.

All the needed optimization steps are performed by an automated software tool, the Onboard Computing Analysis (OCA), which simulates the on-board processing, explores the space of possible combinations of parameters, and produces a set of statistical indicators, among them: the compression rate [math]C_r[/math] and the processing noise [math]\epsilon_Q[/math]. For Planck/LFI it is required that [math]C_r = 2.4[/math] while, as for other systematics, [math]\epsilon_Q \,[/math] would have to be less than 10% of rms of the instrumental white noise. An analytical model is developed that is able to extract most of the relevant information on the processing errors and the compression rate as a function of the signal statistics and the processing parameters to be tuned. This model is of interest for the instrument data analysis to asses the level of signal distortion introduced in the data by the on-board processing.

Once the instrument is completed tuned and stable, a tuning process is applied in order to optimize the REBA parameters. The procedure foresees to acquire chunks of about 15 minutes of averaged data to be analyzed by OCA. After setting the (optimized) REBA parameters, another session of 15 minutes of acquisition is applied, this time with the nominal processing.

The values for the optimal REBA parameters are mainly determined by the frequency of the radiometric channel with some dispersion from detector to detector. Table 13 below gives representative median values for [math]r_1, \, r_2, \, q \, [/math] from on ground System Level tests (CSL) as well as for the quantities in figure 8 below and the resulting data rate. [math] O[/math] is omitted since it is the most variable parameter and it has no significant impact on [math]\epsilon_q[/math] and [math]C_r[/math]. Table 13 below reports also the number of detectors for each frequency channel, the [math]N_{aver}[/math] values which are kept constant, the compressed data rate per detector, per frequency channel and for the instrument as a whole. Quantities are reported in the form [math]x ± \delta x[/math] where [math]\delta x[/math] represents the standard deviation taken as a measure of the internal dispersion of [math]x[/math] within the given subset of detectors, this number must not be interpreted as an error and it must not be propagated.

The performance has been verified against the requirements with the result that the required data rate of 35.5 kbps has been achieved while keeping the processing error at a level of 3.8% of the instrumental white noise and well below the target 10% level.

Figure 8. Results for a typical session of REBA parameters tuning during the CSL test campaign. From top to bottom the figure reports for each detector the mean [math]C_r, \, \epsilon_{q,sky}/\sigma_{sky}, \, \epsilon_{q,load}/\sigma_{load}, \, \epsilon_{q,diff}/\sigma_{diff} \, [/math] where [math]\sigma_{diff}[/math] is the r.m.s. of the differentiated data. The red line in background of the top frame denotes the target [math] C_r^{Tgt} = 2.4[/math]. Values are represented by bars. Light-bars are the results from the calibration phase, where raw data from the instrument are processed by OCA. Dark-bars are results from the verification phase, where processing is performed on-board. The second frame from Top gives an example for detector 00 of Feed-Horn #19. Feed-horns are numbered according to the internal Planck/LFI convention assigning at Planck/LFI the Feed-Horns numbers from #18 to #28. Detectors belonging to the same Feed-Horn are grouped together as shown in the third frame from top.

Table 13. Representative REBA Parameters, the measured [math]C_r[/math] and relative processing errors from the CSL tests for Planck/LFI. Detectors are grouped by frequency channel, for each quantity x the table reports its group median and group standard deviation [math]\delta x[/math] as a measure of the group internal dispersion, [math]\delta x[/math] must be not considered as an error.

In flight the procedure is to acquire continuously data by using the nominal processing. Short chunks of unprocessed data is daily acquired in turn from each detector. The comparison of unprocessed with processed data allows to monitor of the processing error. In addition the REBA tuning might be repeated daily on the chunk of unprocessed data in order to test whether some REBA parameters on-board the satellite should be changed or not.

Instrument Operations

LFI Operational Modes

The operations of the LFI are designed to be automatic and require little if any intervention from the ground. A small amount of commands is required for operating the instrument and eventually for diagnostic and reconfiguration purposes. Each sky survey is conducted by the LFI with the instrument in the Normal Operations Mode mode. No deployable elements, or mechanically moving parts are included in the instrument. The scanning of the sky is achieved by progressive repointing of the satellite spin axis, with the Sun direction always within a cone 10 degrees from the spin axis. Within the Normal Science Mode the instrument can be configured in order to fit with different science or diagnostic needs without changing the power consumption and thus the temperature in the FPU. Changes in power consumption in the FPU are minimised and should occur only in the case that failures in the radiometers that could create interference problems require an RCA to be switched off. Power adjustments on the first stage of the HEMT amplifiers which are contemplated, require extremely small power level variations.

Figure 9. LFI Operating Modes and their nominal transitions

A scheme of the nominal transitions between the LFI Operation Modes are shown in Figure 9, a brief summary is given below.

1. OFF MODE: During this operating mode the instrument is completely off for example during the launch.

2. STAND-BY: During this mode only the REBA can be operated. It is the first interface to the instrument whenever the LFI is switched on. When the instrument is in this mode the RAA must be OFF because no data can be received and no control is possible on the radiometer chains.

3. DAE SET-UP: During this mode the REBA and the DAE are ON, but no radiometer chains are active. Nevertheless science data can be generated and contain only the background noise of the instrument.

4. NORMAL SCIENCE: During this mode the RAA is seen by the REBA as a set of 44 independent instruments. This means that each instrument can be operated, by the same SW, in different modes without affecting the LFI modes. Science data from the DAE are continuously acquired by the REBA that decides, on the basis of the activation table, which packets (either science or diagnostic) have to be produced. The whole set of HK is continuously acquired and sent to ground. This mode is the nominal for the LFI observation operations.

5. EXTENDED SCIENCE: This mode is similar to the previous except that for the total amount of telemetry sent to the ground. In fact this mode shall be used when, in particular cases, (e.g. calibration…) a larger telemetry rate is needed and made available by an agreement with HFI and the CDMS.

During launch, for contingency situations and/or to allow diagnostics of other spacecraft subsystems (e.g. HFI or others) LFI is in the OFF mode. When, upon a command from ground the REBA is powered on, the instrument is in its STAND-BY mode. A step-by-step bootstrap procedure commanded from ground documented by HK is initialized to turn the DAE on. This sets-up the internal communications, and allows the LFI subsystems to collect and deliver a full set of HK. The instrument is in DAE SET-UP mode. The following step is to upload from ground the DAE settings and processing parameters; then, to switch on the RCA on ground command. At this stage, on ground command, the acquisition of science data can start. A further step is needed to move to NORMAL SCIENCE, namely start processing and compressing the science raw data. When this is accomplished, science packets can be sent to ground.

In-flight Operations

TBW

Anomalies

TBW

LFI Ground Tests

During its development, the LFI flight model was calibrated and tested at various integration levels from sub-systems #davis2009 to individual integrated receivers #villa2010 [[Planck pre-launch status: Calibration of the Low Frequency Instrument flight model radiometers] and the whole receiver array #mennella2010 [Planck pre-launch status: Low Frequency Instrument calibration and expected scientific performance]. In every campaign we performed tests according to the following classification:

• Functionality tests, performed to verify the instrument functionality.
• Tuning tests, to tune radiometer parameters (biases, DC electronics gain and offset, digital quantisation and compression) for optimal performance in flight-like thermal conditions.
• Basic calibration and noise performance tests, to characterise instrument performance (photometric calibration, isolation, linearity, noise and stability) in tuned conditions.
• Susceptibility tests, to characterise instrument susceptibility to thermal and electrical variations.

Where possible, the same tests were repeated in several test campaigns, in order to ensure enough redundancy and confidence in the instrument behaviour repeatability. A matrix showing the instrument parameters measured in the various test campaigns is provided in Table 1 of #mennella2010 [Planck pre-launch status: Low Frequency Instrument calibration and expected scientific performance].

The ground test campaign was developed in three main phases: cryogenic tests on the individual RCAs, cryogenic tests on the integrated receiver array (the so-called radiometer array assembly, RAA) and system-level tests after the integration of the LFI and HFI instruments onto the satellite. The first two phases were carried out at the Thales Alenia Space - Italia laboratories located in Vimodrone (Milano, Italy) (note that receiver tests on 70 GHz RCAs were carried out in Finlad, at Yilinen laboratories), system level tests (SLT) were conducted in a dedicated cryofacility at the Centre Spatiale de Liege (CSL) located in Liege (Belgium).

In Table 14 below we list the temperature of the main cold thermal stages during ground tests compared to in-flight nominal values. These values show that system-level tests were conducted in conditions that were as much as possible flight-representative, while results obtained during RCA and RAA tests needed to be extrapolated to flight conditions to allow comparison. Details about the RCA test campaign are discussed in #villa2010 [Planck pre-launch status: Calibration of the Low Frequency Instrument flight model radiometers] while the RAA tests and the extrapolation methods are presented in #mennella2010 [Planck pre-launch status: Low Frequency Instrument calibration and expected scientific performance].

Table 14. Temperatures of the main cold stages during the various ground test campaigns compared to in-flight nominal values

Temperature	Nominal	RCA tests	RAA tests	System-level
Sky	~ 3 K	≳ 8 K	≳ 18.5 K	~ 4 K
Ref. load	~ 4.5 K	≳ 8 K	≳ 18.5 K	~ 4.5 K
Front-end unit	~ 20 K	~ 20 K	~ 26 K	~ 20 K

Cryogenic system-level tests, performed at the cryo-facility of the Centre Spatial de Liège (CSL), were split into three parts:

1. Thermal balance, to validate the overall thermal mathematical model. The ground vacuum test equipment simulated the space environment.

2. System cryogenic test, to check and optimise the satellite and instrument performance working at nominal temperatures.

3. Thermal cycling test, to check the reliability of all electronics equipment and instruments to temperature variations (note that to allow the thermal control of the Service Vehicle Module (SVM), the warm part of the spacecraft was surrounded by a cryogenic shroud at a temperature lower than 100 K. The temperature of the shrouds was adjustable in order to allow the thermal cycling of the SVM during the tests. The temperature ranged between the two extreme values of [math]20^\circ[/math]C to [math]100^\circ [/math]C).

During the various test campaigns the instrument was switched off and moved several times in a time period of about three years. A series of functional tests were always repeated at each location and also in flight, in order to verify the instrument functionality and the response repeatability. No failures or major problems have been identified due to transport and integration procedures.

The expected Planck LFI scientific performance, resulting mainly from cryogenic system level tests, are described in #mennella2010 [Planck pre-launch status: Low Frequency Instrument calibration and expected scientific performance].

LFI In-flight Calibration

The Planck cryo-chain #planck2011-1-3 [Planck early results. The thermal performance of Planck] is composed by three coolers: a 20 K Hydrogen sorption cooler, which is passively pre-cooled by the [math]3^{\rm rd}[/math] V-groove radiator, cools the LFI focal plane and pre-cools the HFI 4K cooler; a Stirling 4K cooler that cools the HFI box and feed-horns and provides a 4K blackbody reference signal to the LFI receivers; a 0.1 K dilution cooler, which is pre-cooled by the 4K cooler and cools the HFI bolometer filters to [math]\sim 1.6[/math]K and the HFI bolometer detectors to ~0.1 K. The cooldown of the HFI 4K stage, in particular, was key during CPV for the LFI as it provided a variable input signal that was exploited during bias tuning.

The LFI CPV started on June, [math]4^{\rm th} \;[/math] 2009 and lasted until August, [math]12^{\rm th} \;[/math] when Planck started scanning the sky in nominal mode. At the onset of CPV, the active cooling started when the radiating surfaces on the payload module reached their working temperatures (~50 K on the [math]3^{\rm rd} \;[/math] V-groove, and ~40 K on the reflectors) by passive cooling. This was achieved during the transfer phase. Nominal temperatures were achieved on July, [math]3^{\rm rd} \;[/math] 2009, when the dilution cooler temperature reached 0.1 K #planck2011-1-3, meinhold2009 [Planck early results. The thermal performance of Planck] (see Figure 5 below).

The CPV was carried out in four phases (see Table 15 below for a summary of the overall CPV test campaign):

• LFI switch on and basic functionality verification,
• Tuning of front-end biases and back-end electronics,
• Preliminary calibration tests,
• Thermal tests.

Table 15. LFI CPV tests

Figure 10. Functional tests performed during CPV against timeline. Curves from thermal sensors monitoring the 4K stage and the FPU temperature are superimposed.

#gregorio2013

TBW

LFI Performance

Instrument Scientific Performance

Optical Parameters

The most accurate measurements of the LFI main beams have been made with Jupiter, the most powerful unresolved (to Planck) celestial source in the LFI frequency range. Since the LFI feed horns point to different positions on the sky, they detect the signal at different times. To map the beam, each sample in the selected timelines was projected in the [math] (u, \, v)[/math]-plane perpendicular to the nominal line-of-sight (LOS) of the telescope (and at 85◦ to the satellite spin axis). The [math] u[/math] and [math] v [/math] coordinates are defined in terms of the usual spherical coordinates [math] (θ, φ)[/math] :

[math] u = sinθ \, cosφ, [/math]

[math] v = sinθ \, sinφ. [/math]

To increase the signal-to-noise ratio, data were binned in an angular region of 2′ for the 70 GHz channels and 4′ for the 30 and 44 GHz channels. We recovered all beams down to −20 dB from the peak. An elliptical Gaussian was fit to each beam for both M and S radiometers. The FWHM given in table 16 is the square root of the product of the major axis and minor axis FWHMs of the individual beams, averaged between M and S radiometers. The uncertainties in Table 16 are the standard deviation of the mean of the 1σ statistical uncertainties of the fit. Differences between the M and S beams caused by optics and receiver non-idealities are inevitable at some level, but they appear to be well within the statistical uncertainties, and for the purposes of point-source extraction relevant for this paper, the beams may be considered identical. Table 16 (#planck2011-1-4 [Planck early results. First assessment of the Low Frequency Instrument in-flight performance]) gives the typical FWHM and ellipticity averaged over each frequency channel. Exhaustive details on all LFI beam parameters are presented in the LFI data processing section - Beams.

Table 16. LFI beam FWHM and mean ellipticity measured in flight from the first Jupiter pass.

Photometric Calibration

Photometric calibration, i.e., conversion from voltage to antenna temperature, is performed for each radiometer after total power data have been cleaned of 1 Hz frequency spikes (see the LFI data processing section - Spikes Removal section and #planck2011-1-6 [Planck early results. The Low Frequency Instrument data processing]), and differenced. Here we report a brief overview of the photometric calibration, for the details see the LFI data processing section - Photometric Calibration.

Our calibrator is the well-known dipole signal induced by Earth and spacecraft motions with respect to the CMB rest frame. The largest calibration uncertainty comes from the presence of the Galaxy and of the CMB anisotropies in the measured signal. We therefore use an iterative calibration procedure in which the dipole is fitted and subtracted, producing a sky map that is then removed from the original data to enhance the dipole signal for the next iteration. Typically, convergence is obtained after a few tens of iterations.

In our current calibration model we use as calibration signal the sum of the solar dipole [math]\Delta T_{Sun}[/math] and the orbital dipole [math]\Delta T_{orb}[/math], which is the contribution from Planck’s orbital velocity around the Sun,

[math] \label{eq:cal1} \Delta T= ( \Delta T_{Sun} + \Delta T_{orb} ) sin \theta_{axis} [/math]

where [math]\theta_{axis}[/math] is the angle between the spacecraft axis and the overall dipole axis (solar + orbital). In this equation, the absolute calibration uncertainty is dominated by the uncertainty in [math]T_{Sun}[/math] = 3.355 mK ± 0.008 mK hinshaw2009, which is known to about 0.2%. The modulation of the orbital dipole by the Earth motion around the Sun is known with an uncertainty almost three orders of magnitude smaller; however, at least one complete Planck orbit is needed for its measurement. The accuracy of our current calibration can be estimated by taking into account two components: 1) the statistical uncertainty in the regions of weak dipole; and 2) the systematic uncertainty caused by neglecting gain fluctuations that occur on periods shorter than the smoothing window. In our calibration procedure the gain is estimated for every pointing period: if we call [math] G_i [/math] the gain estimate from the [math]i_{th}[/math] pointing period we have that the associated uncertainty is

[math] \label{eq:cal2} \delta G = \sqrt{\frac{ \Sigma_{i=1}^N (G_i-\lt G\gt )^2 }{N-1} } [/math]

where [math]N[/math] is the overall number of pointing and [math]\lt G\gt [/math] is the average of the [math]N[/math] gains. We then approximate the effect of the smoothing filter as an average over [math]M[/math] consecutive pointings, so that the overall uncertainty can be estimated as:

[math] \label{eq:cal3} \delta G |_{stat} = \frac{\delta G}{\sqrt{M}} = \frac{1}{\sqrt{M}} \sqrt{\frac{ \Sigma_{i=1}^N (G_i-\lt G\gt )^2 }{N-1} } [/math]

Table 17 lists the largest statistical uncertainties in four time windows (days 100–140, 280–320, 205–245, 349–389), the first two corresponding to minimum and the second two to maximum dipole response. In order to provide conservative estimates we have always chosen a value for [math]M[/math] corresponding to the number of pointings in 5 days also in the cases where a 30-day smoothing window was used.

Table 17. Worst case relative calibration uncertainties.

Noise Properties

The noise characteristics of the LFI datastreams are closely reproduced by a simple (white + [math]1/ f[/math] ) noise model,

[math] \label{eq:p1} P(f)= \sigma^2 (1+ (\frac{f}{f_{knee}})^\alpha ) [/math]

where [math]P( f )[/math] is the power spectrum and [math]α ≈ −1[/math]. In this model, noise properties are characterised by three parameters, the white noise limit [math]\sigma[/math], the knee frequency [math]f_{knee}[/math], and the exponent of the [math]1/ f[/math] component [math]\alpha[/math], also referred to as slope. Here we give noise performance estimates based on one year of operations, details of the analysis are given in LFI data processing section - Noise Estimation and in #planck2011-1-6, planck2011-1-4 [Planck early results. The Low Frequency Instrument data processing, Planck early results. First assessment of the Low Frequency Instrument in-flight performance].

Noise properties have been calculated following two different and complementary approaches: 1) fitting equation above to time-ordered data for each radiometer; and 2) building normalised noise maps by differencing data from the first half of the pointing period with data from the second half of the pointing period to remove the sky signal (“jackknife” data sets).

Results for [math]\sigma, \, f_{knee} [/math], and [math]\alpha [/math], after one year of operations for all LFI radiometers, are given in Tables 17 and 18 below. Typical uncertainties are ∼0.5% for the white noise, between 5 and 10% for the slope, and between 10 and 20% for the knee frequency. Comparing the noise power spectra for all 22 LFI radiometers with their best-fit model, we found good agreement.

Table 17. White noise sensitivities for the LFI radiometers.

Table 18. Knee frequency and slope for the LFI radiometers.

White Noise Sensitivity

As detailed in #planck2011-1-4 [Planck early results. First assessment of the Low Frequency Instrument in-flight performance], figure 13 compares the calibrated white noise sensitivity for the 22 LFI radiometers calculated from flight data and during ground tests performed both at instrument and satellite level. Error bars reported for values measured in flight and during satellite tests are statistical uncertainties derived from calculations performed on about 20 one-hour blocks of on-ground satellite data and one year of in-flight data. Error bars reported for values measured at instrument level, instead, represent the uncertainty between two different methods used to extrapolate the white noise sensitivity measured at test conditions (∼20 K input and ∼26 K front-end temperature) to flight conditions (∼2 K input and ∼20 K front-end temperature). Figure 13 shows general agreement in the sensitivity calculated in various test campaigns, with two outstanding exceptions, radiometers LFI24M and LFI21S, which show significantly improved noise levels in-flight. This resulted from an incorrect bias setting of these radiometers during ground tests, which was resolved during in-flight tuning. In figure 13 values for LFI18M and LFI24M measured at instrument-level are not reported because these two radiometers failed. LFI18M was replaced with a spare unit and LFI24M was repaired before instrument delivery.

Figure 11. Comparison of white noise sensitivity values calculated in flight and on ground during the satellite-level and instrument-level test campaigns. Values for LFI18M and LFI24M measured at instrument-level are not reported because these two radiometers failed before instrument delivery and were replaced and repaired, respectively.

Table 19 summarizes the sensitivity numbers calculated during the first year of operations using methods and procedures described in detail in #planck2011-1-6 [Planck early results. The Low Frequency Instrument data processing], compared with scientific requirements. The measured sensitivity is in very good agreement with pre-launch expectations. While the white noise moderately exceeds the design specification, this performance is fully in line with the LFI science objectives.

Table 19. White noise sensitivity of the LFI frequency channels compared with requirements.

Instrument Technical Performance

Spectral Response

The in-band receiver response has been thoroughly modelled and measured for all the LFI detectors during ground tests. The complete set of bandpass curves has been published in #zonca2009 where all the details of the LFI radiometer's spectral response are given. From each curve we have derived the effective centre frequency according to:

[math] \label{eq:spectr} \nu_0 = \frac{ \int_{\nu_{min}}^{\nu_{max}} \nu g(\nu) \; d \nu} {\int_{\nu_{min}}^{\nu_{max}} g(\nu)\; d\nu } [/math]

where [math] \Delta \nu = \nu_{max} − \nu_{min} \;[/math] is the receiver bandwidth and [math]g(\nu)\;[/math] is the bandpass response. Table 18 below gives the centre frequencies of the 22 LFI radiometers. For each radiometer, [math] g(\nu)\;[/math] is calculated by weight-averaging the bandpass response of the two individual diodes with the same weights used to average detector timestreams. For simplicity and for historical reasons, we will continue to refer to the three channels as the 30, 44, and 70 GHz channels.

Table 18. LFI centre frequencies.

Colour corrections, [math]C(\alpha)[/math] , needed to derive the brightness temperature of a source with a power-law spectral index [math]\alpha[/math], are given in the table 19 below. The values are averaged for the 11 RCAs and for the three frequency channels. Details about the definition of colour corrections are provided in #planck2011-1-6.

Table 19. Colour corrections for the 11 LFI RCAs individually and averaged by frequency.

Bandpass Estimation

As detailed in #zonca2009, our most accurate method to measure the LFI bandpasses is based on measurements of individual components integrated into the LFI Advanced RF Model (LARFM) to yield a synthesised radiometer bandpass. The LARFM is a software tool based on the open-source Quasi Universal Circuit Simulator (QUCS). The measured frequency responses of the various subsystems (feed-OMT, FEM, BEM) are considered as lumped S-parameter components. Measurements of single components are obtained with standard methods and provide highly reliable results, with precision of order 0.1-0.2 dB over the entire band. Waveguides are simulated with an analytical model, in order to reproduce the effect of their temperature gradient and the effect of standing waves caused by impedance mismatch at the interfaces between the FEM and BEM. This is because the 1.8-meter long waveguides were not measured at unit level in cryogenic conditions. The model provides accurate agreement with the measured waveguide response in the conditions of the test measurements (300 K). The composite bandpasses are estimated to have a precision of about 1.5 to 2 dB.

We also attempted an end-to-end measurement of the RCA spectral response in the cryo-facility as an independent check. Unfortunately, these measurements suffered some subtle systematic effects in the test setup (standing waves at 70 GHz; polarisation mismatch and narrow frequency coverage at 30 and 44 GHz), preventing an accurate cross-check. However, the comparison shows a general agreement within limits of the test reliability and repeatability.

Figures 12 and 13 below show all the LFI bandpasses obtained by the frequency response data of each radiometer unit assembled by the LARFM. The 70 GHz channels show a low bandpass ripple, of about 10 dB, which is within scientific requirements. The spike between 60 and 61 GHz, below the low frequency cut-off, is due to a systematic effect present in all the BEM gain measurements and caused by the test setup. We removed this range from the bandpasses made available at the Data Processing Center in order to avoid possible spurious effects and therefore the frequency coverage is 61-80 GHz. The high frequency cut-off is not well defined in most of the channels. The 30 and 44 GHz bandpasses show a more complex shape, driven by the BEM spectral response, but still within [math]\pm 10[/math] dB. The low frequency cut-off is always well defined, while the high frequency cut-off is not well defined in RCA 24 and 26. However, comparing with the high frequency cut-off of RCA 25, it is expected that the additional bandwidth is very low. Frequency coverage is 25-50 GHz for the 44 GHz channels and 21.3-40 GHz for the 30 GHz channels.

Figure 12. LFI 70 GHz channels’ bandpasses. Each row shows the 4 bandpasses of a RCA ordered as M-00, M-01, S-10 and S-11. Units are [dB] [math]10log(\frac{V_{out}}{V_{in}})[/math] plotted against frequency [GHz].

Figure 13. LFI30 and 44 GHz channels’ bandpasses. Each row shows the 4 bandpasses of a RCA ordered as M-00, M-01, S-10 and S-11. Units are [dB] [math]10log(\frac{V_{out}}{V_{in}})[/math] plotted against frequency [GHz].

Stability

Thanks to its differential scheme, the LFI is insensitive to many effects caused by 1/f noise, thermal fluctuations, or electrical instabilities. As detailed in #planck2011-1-4 [Planck early results. First assessment of the Low Frequency Instrument in-flight performance], one effect detected during the first survey was the daily temperature fluctuation in the back-end unit induced by the downlink transponder, which was powered on each day for downlinks during the first 258 days of the mission. As expected, the effect is highly correlated between the sky and reference load signals. In the difference, the variation is reduced by a factor [math]∼(1 − r)[/math], where [math]r[/math] is the gain modulation factor defined above.

A particular class of signal fluctuations occasionally observed during operations is due to electrical instabilities that appear as abrupt increases in the measured drain current of the front-end amplifiers, with a relaxation time variable from few seconds to some hundreds of seconds. Typically, these events cause a simultaneous change in the sky and reference load signals. Because they are essentially common-mode, their residual on the differenced data is negligible (figure 14), and the data are suitable for science production. In a few cases the residual fluctuation in the differential output was large enough (a few millikelvin in calibrated antenna temperature units) to be flagged, and the data were not used. The total amount of discarded data for all LFI channels until Operational Day 389 was about 2000 s per detector, or 0.008%.

A further peculiar effect appeared in the 44 GHz detectors, where single isolated samples, either on the sky or the reference voltage output, were far from the rest. Over a reference period of four months, 15 occurrences of single-sample spikes (out of 24 total anomaly events) were discarded, an insignificant loss of data.

Figure 14. Short spikes in the drain current (left) affect total power signals (right). The jumps are strongly correlated in sky and reference signals, so that in the difference data the effect essentially disappears.

Thermal Susceptibility

As already mentioned in section LFI In-flight Calibration above and detailed in #gregorio2013, during the CPV campaign, susceptibility tests were performed in order to characterise the LFI instrument susceptibility to thermal and electrical variations.

The effect of temperature fluctuations on the LFI radiometers is originated in the Planck cold end interface of the hydrogen sorption cooler to the instrument focal plane. The temperature is actively controlled through a dedicated stage, the Thermal Stabilization Assembly (TSA), providing a first reduction of the effect. The thermal mass of the focal plane strongly contribute to reduce residual fluctuations. The physical temperature fluctuations propagated at the front end modules cause a correlated fluctuation in the radiometer signal degrading the quality of scientific data. The accurate characterization of this effect is crucial for possibly removing it from raw data by exploiting the housekeeping information of thermal sensors.

The propagation of the temperature oscillations through the focal plane and the instrument response to thermal changes were characterized through two main tests:

• the thermal dynamic response aimed at measuring the dynamic thermal behaviour of the LFI Focal Plane;
• the radiometers thermal susceptibility.

Thermal Dynamic Response

In order to amplify the effect and to get a more accurate measurement, the active control from the TSA was switched off. The resulting increased fluctuations, propagating at the cooler frequencies, were used to evaluate transfer functions between the TSA stage and the FPU sensors (see figure 14 below). The analysis produced damping factors of 2–5 at about 1 mHz. The source of fluctuations was characterized by two typical periods of the sorption cooler during the final CPV phase: (i) the single bed cycle time, 940 s, (ii) the complete cooler period, six times larger, 5640 s.

Figure 14. Schema of the focal plane thermal sensor locations.

Results are shown in Table 20. Sorting the sensors by the transfer function amplitudes in descending order (second column of the table), the route of the propagation of temperature fluctuations through the focal plane sensors (shown in figure 14) was reproduced as expected: the largest amplitudes are in the sensor closest to the right bottom corner interface with the working cooler and they decrease in the direction left upwards. The measured values in flight showing a good agreement with what measured during the CSL ground test.

Table 20. Transmission amplitudes and phases of fluctuations at the two main cooler frequencies during the transient test. Typical fit parameters uncertainties are at 1% level.

Radiometer Thermal Susceptibility

Fluctuations of the focal plane temperature would cause variations of important parameters (mainly the low noise amplifier gains and noise temperatures), impacting the radiometer output signal. The response of the LFI radiometers to thermal fluctuations was estimated by inducing discrete temperature steps on the focal plane through TSA set-point changes. The set-point was changed over four values (Fig. 47, left) and after a stabilization of at least two hours, the measured receivers output was characterized as a function of each temperature variation of about 0.3 K.

The slope of the resulting [math]T_{ant} [/math] vs [math]T_{phys} [/math] plot is the measured response of the receivers to a change in the temperature. Results, reported in the Table 21, confirmed that physical temperature fluctuations in the main frame are furtherly reduced when convolved with the radiometer thermal susceptibility coefficients: the derived output fluctuations, measured in antenna temperature, were actually reduced by an extra factor of 10 to 200 (according to the channel considered), of the same order of ground test results. This corresponds to reduce the mean peak-to-peak amplitudes of fluctuations measured by high resolution sensors, of the order of 4 mK in steady condition, of at least one order of magnitude in the output timestream.

Table 21. Results of thermal susceptibility test. Units are [math]K_{ant}/K_{phys}[/math]. Together with the radiometers, the closest sensor used as reference for the physical temperature is indicated. Results for the detector LFI24S-11 are missing because it suffered a period of signal saturation during the test.

Instrument Budgets

Power Budget

Table 22. LFI sub-system power budget.

Subsystem	Unit	Assembly	Sub-Assembly	Budget [W]
RAA				45.599
	FEU			0.329
		FE structure		N/A
		Feed Horns		N/A
		OMTs		N/A
		FEMs		0.329
			30 GHz	0.056
			44 GHz	0.121
			70 GHz	0.152
	BEU			45.270
		DAE		31.986
		BEMs		13.284
			30 GHz	4.914
			44 GHz	4.633
			70 GHz	3.737
		Waveguides		N/A
		RAA harness		N/A
	4K Load			N/A
REBA				22.700
System Harness				N/A
Total				68.299

Mass Budget

The maximum allocated mass for the Planck Instruments is 445 kg, 89 kg are allocated for the LFI instrument. The distribution of the instrument and cooler mass to the different interfaces in the system is as given in table 23 below.

Table 23. LFI sub-system mass budget.

Subsystem	Unit	Assembly	Sub-Assembly	Budget [kg]
RAA				77.900
	FEU			22.935
		FE structure		17.680
		Feed Horns+OMTs		2.825
			30 GHz	0.680
			44 GHz	0.732
			70 GHz	1.413
		FEMs		2.430
			30 GHz	0.810
			44 GHz	1.110
			70 GHz	0.510
	BEU			25.542
		DAE		23.130
		BEMs		2.412
			30 GHz	0.624
			44 GHz	0.864
			70 GHz	0.924
	Waveguides			23.005
		WG structure		15.940
		WGs		7.065
	RAA harness			5.491
		BEU internal harness		4.489
		DAE-FEU cryo-harness		1.002
	4K Load			0.927
REBA (2 units)				8.480
System Harness				3.495
Total				89.875

Telemetry Budget

All the science data flow coming from the foreseen on-board data processing can be summarised in the following table 24.

Table 24. Data processing and compression results.

	30 GHz	44 GHz	70 GHz	Total
Total samples	65	94	154
Compression factor	2.4	2.4	2.4
Compressed samples	27	39	64
Science data available (word)	490	490	490
Time per packet (s)	18.035	12.570	7.651
Corresponding sky arc ([math]^\circ[/math])	108	75	46
Packet frequency (Hz)	0.444	0.955	3.317
Net Data Volume (word/s)	217.352	467.778	1536.986	2222.116
Net Data Volume (kbps)	3.478	7.484	24.592	35.554

This result refers to the net science telemetry rate that LFI sends to ground. If we add the overhead due to the packet header (protocol) and the tertiary header we obtain a gross science telemetry rate of 37.150 kbps. This number should be added to the data coming from the calibration channel (uncompressed data used to verify the correct functionalities of the on-board compression algorithm, see Reduction and Compression of Science Data section) sent to ground in parallel. This channel has a worst case gross data production of 5.140 kbps for a total science data of 42.290 kbps.

The gross housekeeping telemetry budget is 2.425 kbps for a total budget of 44.715 kbps. The total data budget allocated to the LFI is 53.5 kbps well above the LFI total telemetry budget.

LFI Systematics Effects

The LFI design was driven by the need to suppress systematic effects well below instrument white noise. The differential receiver scheme, with reference loads cooled to 4 K, greatly minimises the effect of 1/f noise and common-mode fluctuations, such as thermal perturbations in the 20K LFI focal plane. The use of a gain modulation factor (see Eq. \ref{eq:erre1} in RCA section above) largely compensates for spurious contributions from input offsets. Furthermore, diode averaging (Eq. \ref{eq:v1} in RCA section above) allows us to cancel second-order correlations such as those originating from phase switch imbalances.

We have developed an error budget for systematic effects (#planck2011-1-4, bersanelli2010 [Planck early results. First assessment of the Low Frequency Instrument in-flight performance],Planck pre-launch status: Design and description of the Low Frequency Instrument]) as a reference for both instrument design and data analysis. Our goal is to ensure that each systematic effect is rejected to the specified level, either by design or by robust removal in software. At this stage, the following effects are relevant:

– 1/f noise;

– 1 Hz frequency spikes;

– receivers non-linearities;

– thermal fluctuations in the back-end modules driven by temperature oscillations from the transponder during the first survey;

– thermal fluctuations in the 20 K focal plane;

– thermal fluctuations of the 4 K reference loads.

For each of these effects we used flight data and information from ground tests to build timelines, maps, and angular power spectra that represent our best knowledge of their impact on the scientific analysis. The details of the systematic effect analysis is given in section LFI data processing section - Systematic Effects uncertainties.

Acronyms

BEM Back End Module

BEU Back End Unit

CCE Central Check-out Equipment

CDMS Command and Data Management Subsystem

CDMU Central Data Management Unit

CoG Centre of Gravity

CPV Calibration and Performance Verification

CSL Centre Spatiale de Liege

DAE Data Acquisition Electronics

DC Direct Current

DPC Data Processing Centre

EMC Electro-Magnetic Compatibility

EMI Electro-Magnetic Interference

FEM Front End Module

FEU Front End Unit

FH Feed Horn

FOV Field Of View

FPU Focal Plane Unit

HK House Keeping

ILT Instrument Level Test

IST Integrated System Test

JFET Junction Field Effect Transistor

LEOP Launch and Early Orbit Phase

MLI Multilayer Insulation

MoI Moment of Inertia

MOS Margin Of Safety

OMT Ortho Module Transducer

PCS Power Control Subsystem

PSF Point Spread Function

RAA Radiometer Array Assembly

RAM Random Access Memory

RCA Radiometer Chain Assembly

REBA Radiometer Electronics Box Assembly

S/C Spacecraft

SCC Sorption Cooler Compressor assembly

SCCE Sorption Cooler Cold End

SCE Sorption Cooler Electronics

SCOS Spacecraft Control and Operations System

SCP Sorption Cooler Piping

SCS Sorption Cooler Subsystem

SLT System Level Test

SS Stainless Steel

SVM Service Module

TCS Thermal Control System

TM Telemetry

TSA Thermal Stabilization Assembly

TTC Telemetry, Tracking and Command

VSWR Voltage Standing Wave Ratio

WG Waveguide

Glossary

Feed Horns xxx

REBA Radiometer Electronics Box Assembly

References

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1. References

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