Ariel payload harness thermal analysis

This document describes the results of the thermal analysis of the Ariel payload harness. The evaluations reported in this Technical Note are based on assumptions derived from the present knowledge of the subsystems architecture, scientific requirements and performances expected on the basis of previous experiments and results. This is a living document that has the function to report the details of the payload cables thermal analysis. It will follow the evolution of the harness design, characteristics and performances from the thermal point of view during the Ariel payload design consolidation process. Keywords: thermal design and analysis, thermal model, spacecraft thermal control, cryogenics, exoplanets, infrared spectroscop

Planck sorption cooler system user manual

Keywords: space cryogenics, space operations, space instrumentation, thermal control, CMB cosmolog

Planck sorption cooler system cop and cpv test plan

This document describes the test sequence and procedures of the Planck Sorption Cooler System during Commissioning (COP) and Calibration (CPV) Phases in flight. COP and CPV timelines depend on the specific subsystem considered: SCS, for example, will complete its commissioning and verification phases well before the instruments. For this reason, it will enter Routine Operations when HFI and LFI will still be in their CPV. For each in-flight SCS test or activity all needed info is reported in a table containing test name, description, constraints, duration, pass/fail criteria, operational requirements, procedures etc

Planck sorption cooler system tv/tb test procedures at csl

planned for the thermal vacuum cryogenic test campaign at CSL. Each Chapter is dedicated to a specific Phase of the Test Campaign. For each Phase in which the SCS is operated is shown a summary of: Rationale, Objective, Configuration of SVM and PLM needed, Thermal boundaries, Pass/fail criteria, Duration

Planck sorption cooler flight model 1 flight model 2 verification plan

This document is intended to contain the results of the tests of the Planck Sorption Cooler. This is comprised of the Thermal Mechanical Unit (TMU) and the LPSC flight electronics (SCE). JPL is directly responsible for testing the TMU only while providing test time for the electronics unit, for which the LPSC is responsible. The compliancy to the requirements is also reported

Planck sorption cooler inflight performance prediction report

The scope of this document is to show the predictions of inflight performance of the Sorption Cooler subsystem as a consequence of analysis, the Subsystem Testing and Unit testing, and the Planck System Level Thermal Vacuum, Thermal Balance, and Cryogenic verification campaigns. These predictions will be compared with the specifications as required by ESA to demonstrate that the Sorption Cooler will operate as expected in the mission

Planck sorption cooler engineering breadboard test report

In order to validate the sorption cooler flight design, an Engineering Breadboard (EBB) cooler was developed. Testing of the EBB cooler began in January, 2002, and ended in May, 2003. Throughout this period, the cooler was operated for a total of 4300 hours, during which its performance was verified with respect to the flight requirements. Prior to its construction, all of its components and sub-assemblies were tested individually. Interaction among these subsystems was yet to be validated. The EBB provided this system test prior to the construction of the flight models. In addition, operation of the EBB was used to develop robust operational algorithms, which were implemented in the flight prototype electronics. The prototype electronics were validated by testing with the EBB cooler. All the components for the flight cooler have been built to be functionally equivalent to those of the EBB, with a few exceptions. For this reason, the subassembly interactions and performance in the EBB are considered to be representative of those expected of the flight models. The impact of the differences between the EBB and flight models will be assessed in the following sections. All lessons learned from the EBB tests were implemented in the design and operation of the flight cooler

LFI End of Life Activities Definition

This document describes the activities to be performed on LFI at the End of Life of the Planck satellite. The starting condition of LFI is considered to be “Nominal”. The aim of this document is to describe in detail the operations that are required to be performed at the End of Life on LFI. Each activity is ultimately broken down to the procedure level, and all inputs are defined. The starting conditions for each activity stage are defined, as well as the activity constraints and conditions, for example the temperature range within which the activity shall be performed. Due to the complexity of some (tuning) activities, the MOC operations will be pre-prepared using proprietary application that will construct a Manual Stack with all of the commands specific to the particular ‘tuning activity’ of an activity stage. The commands for some tuning activities will be time-tagged, and will execute from the on-board MTL. This allows the activities to be controlled more efficiently, and of course accommodates the long duration execution of some activities. The commanding activities for a particular stage may involve both real-time command execution, together with MTL commanding. In all cases the complete activity stage will be prepared in advance. The ‘commanding products’ produced prior to each activity stage will be sent to LFI for formal approval prior to uplink

Preliminary evaluation of the impact of temperature fluctuations in the HFI 4Kstage on LFI

In this technical note we provide a preliminary analysis of the effect of temperature fluctuations at the level of the HFI 4K stage on the scientific performances of the Planck-LFI instrument. The stability of this stage is of crucial importance for the LFI, as it impact directly the stability of the measured signal through its reference load. The availability of the first simulations of the 4K temperature stability from the HFI team has prompted a quick assessment of the expected effect, which is found to be large enough to require the application of software removal algorithms to maintain the residual effect in the final maps within the required levels. Clearly it is of crucial importance the availability in a short time of measurements from the HFI 4K cooler in order to be able to perform robust estimates of the final expected systematic effect

Temperature stability requirements at the interface between the ECCOSORB sky-load and its support in the LFI cryofacility

During the testing phase of the QM and FM LFI instrument, the integrated radiometer chain assemblies (RCAs) will be tested in a dedicated cryo facility. The input signal will be provided by an eccosorb load placed in front of the LFI feed horns that simulates the sky signal; the thermal stability of this sky load needs to be of the same order of the stability that is expected in flight for the primary and secondary mirrors, in order not to introduce uncertainties in the test results that may be difficult to interpret. In this document we derive the thermal stability requirements at the interface between the ECCOSORB sky load and its support starting from the signal stability requirements and considering the current knowledge concerning thermal conduction properties of the ECCOSORB at 20 K