The Raman Laser Spectrometer (RLS) is one of the Pasteur Payload instruments within the ESA’s ExoMars mission. The RLS instrument scientific goal consists of perform in-situ Raman spectroscopy over different organic and mineral powder samples of the Mars subsoil. It consists of three main units: SPU (Spectrometer Unit), iOH (Internal Optical Head), ICEU (Instrument Control and Excitation Unit) which are interconnected by an optical and electrical harnesses (OH and EH).
The SPU is one of the most critical units of the RLS instrument. The Engineering Qualification Model (EQM) unit has been already delivered after a proper qualified campaign in a very demanding environment with very restrictive design constraints, including Planetary Protection requirements. Also, a complete set of functional tests had been carried out under representative environment, simulating not only Mars rover´s laboratory conditions (thermal range and pressure), but also the cruise phase. Previously, an exhaustive qualification campaign was developed with two different purposes: to mitigate the risks associated to new optical elements included in the design and without space heritage; and to obtain a detailed comprehension of their behaviour under Mars conditions for facing the Flight Model (FM) optical design with guarantee of success.
EQM results were successful in terms of Engineering, and a SWaP-optimized system had been reached. The acquired knowledge of that model has been used to implement little improvements into SPU FM for acceptance. For operations, a big amelioration has been the reduction of the image ROI on the Charge-Coupled Device (CCD) after the improving of the alignment of the inclination degree of the image plane on CCD under the tightly integration constrains, letting to download the minimum necessary data bytes. These improvements achieved by a proper analysis of the image on the SPU CCD will allow to evaluate far better the Raman spectrum effects.
SPU FM Mechanical, Thermal-Vacuum campaign has been already finished in order to accept for flight the current unit which will be already completed and “flight qualified” at RLS system level before the congress. If everything continues on this way, the desired Technology Readiness level, TRL 8 maturity level, will be reported during the following text.
The objective of this report is to present the study performed for a specially demanding solution of a spectrometer [1] design based on a transmissive holographic grating especially designed to actuate as the dispersion element. The main driver of the design has been to obtain a device with a clear reduction in mass, power and mechanical envelope with respect to the previous configuration based on a prism and/or Echelle grating. This simplification is produced mainly at expense of the waveband range. This study has been carried out by Laboratorio de Instrumentación Espacial (LINES) optical designers from Instituto Nacional de Técnica Aeroespacial (INTA).
F. Rull, A. Sansano, E. Díaz, C. P. Canora, A. Moral, C. Tato, M. Colombo, T. Belenguer, M. Fernández, J. A. R. Manfredi, R. Canchal, B. Dávila, A. Jiménez, P. Gallego, S. Ibarmia, J. A. Prieto, A. Santiago, J. Pla, G. Ramos, C. Díaz, C. González
The Raman Laser Spectrometer (RLS) is one of the Pasteur Payload instruments, within the ESA's Aurora Exploration
Programme, ExoMars mission.
ExoMars 2018 main Scientific objective is "Searching for evidence of past and present life on Mars".
Raman Spectroscopy is used to analyze the vibrational modes of a substance either in the solid, liquid or gas state. It
relies on the inelastic scattering (Raman Scattering) of monochromatic light produced by atoms and molecules. The
radiation-matter interaction results in the energy of the exciting photons to be shifted up or down. The shift in energy
appears as a spectral distribution and therefore provides an unique fingerprint by which the substances can be identified
and structurally analyzed.
The RLS is being developed by an European Consortium composed by Spanish, French, German and UK partners. It will
perform Raman spectroscopy on crushed powdered samples inside the Rover's Analytical Laboratory Drawer.
Instrument performances are being evaluated by means of simulation tools and development of an instrument prototype.
E. Díaz, A. Moral, C. Canora, G. Ramos, O. Barcos, J. A. Prieto, I. B. Hutchinson, R. Ingley, M. Colombo, R. Canchal, B. Dávila, J. A. R. Manfredi, A. Jiménez, P. Gallego, J. Pla, R. Margoillés, F. Rull, A. Sansano, G. López, A. Catalá, C. Tato
The Raman Laser Spectrometer (RLS) is one of the Pasteur Payload instruments, within the ESA's Aurora Exploration
Programme, ExoMars mission.
The RLS Instrument will perform Raman spectroscopy on crushed powdered samples deposited on a small container
after crushing the cores obtained by the Rover's drill system.
In response to ESA requirements for delta-PDR to be held in mid 2012, an instrument BB programme has been
developed, by RLS Assembly Integration and Verification (AIV) Team to achieve the Technology Readiness level 5
(TRL5), during last 2010 and whole 2011. Currently RLS instrument is being developed pending its CoDR (Conceptual
Design Revision) with ESA, in October 2011.
It is planned to have a fully operative breadboard, conformed from different unit and sub-units breadboards that would
demonstrate the end-to-end performance of the flight representative units by 2011 Q4.
F. Rull, A. Sansano, E. Díaz, M. Colombo, T. Belenguer, M. Fernández, V. Guembe, R. Canchal, B. Dávila, A. Sánchez, H. Laguna, G. Ramos, C. González, D. Fraga, P. Gallego, I. Hutchinson, R. Ingley, J. Sánchez, C. Canora, A. Moral, S. Ibarmia, J. A. Prieto, J. A. R. Manfredi, P. Cabo, C. Díaz, A. Jiménez, J. Pla, R. Margoillés
The Raman Laser Spectrometer instrument is included in ExoMars program Pasteur payload and it is focused on the
Mars samples analytical analysis of the geochemistry content and elemental composition of the observed crushed
samples obtained by the Rover.
One of the most critical Units of the RLS is the Spectrometer unit (SPU) that performs Raman spectroscopy technique
and operates in a very demanding environment (operative temperature: from -40 ºC to 6 ºC) with very restrictive design
constraints. It is a very small optical instrument capable to cope with 0.09 nm/pixel of resolution. The selected solution is
based on a single transmisive holographic grating.
At this stage of the project SPU Team is preparing the Conceptual Design Review that will take place at the end of
October 2011.
F. Rull, A. Sansano, E. Díaz, C. Canora, A. Moral, C. Tato, M. Colombo, T. Belenguer, M. Fernández, J. A. Manfredi, R. Canchal, B. Dávila, A. Jiménez, P. Gallego, S. Ibarmia, J. A. Prieto, A. Santiago, J. Pla, G. Ramos, C. González
The Raman Laser Spectrometer (RLS) is one of the Pasteur Payload instruments, within the ESA's Aurora Exploration
Programme, ExoMars mission.
The RLS Instrument will perform Raman spectroscopy on crushed powered samples deposited on a small container after
crushing the cores obtained by the Rover's drill system. This is the first time that a Raman spectrometer will be launched
in an out planetary mission.
The Instrument will be accommodated and operate inside the Rover's ALD (Analytical Laboratory Drawer), complying
with COSPAR (Committee on Space Research) Planetary Protection requirements.
The RLS Instrument is composed by the following units: SPU (Spectrometer Unit); iOH: (Internal Optical Head); ICEU (Instrument Control and Excitation Unit).
Other instrument units are EH (Electrical Harness), OH (Optical Harness) and RLS SW On-Board.
T. Belenguer, M. A. Alcacera, A. Aricha, A. Balado, J. Barandiarán, A. Bernardo, M. R. Canchal, M. Colombo, E. Diaz, V. Eiriz, I. Figueroa, G. García, A. Giménez, L. González, F. Herrada, A. Jiménez, R. López, M. Menéndez, M. Reina, J. A. Rodríguez, A. Sánchez
KEYWORDS: Space telescopes, James Webb Space Telescope, Mirrors, Telescopes, Device simulation, Integrating spheres, Control systems, Molybdenum, Imaging systems, Interfaces
The MTS, MIRI Telescope Simulator, is developed by INTA as the Spanish contribution of
MIRI (Mid InfraRed Instrument) on board JWST (James Web Space Telescope).
The MTS is considered as optical equipment which is part of Optical Ground Support
Equipment for the AIV/Calibration phase of the instrument at Rutherford Appleton
Laboratory, UK.
It is an optical simulator of the JWST Telescope, which will provide a diffractionlimited test
beam, including the obscuration and mask pattern, in all the MIRI FOV and in all defocusing
range. The MTS will have to stand an environment similar to the flight conditions (35K) but
using a smaller set-up, typically at lab scales.
The MTS will be used to verify MIRI instrument-level tests, based on checking the
implementation/realisation of the interfaces and performances, as well as the instrument
properties not subject to interface control such as overall transmission of various modes of
operation.
This paper includes a functional description and a summary of the development status.
F. Herrada, V. Eiriz, M. Alcacera, A. Aricha, A. Balado, J. Barandiaran, T. Berenguer, E. Diaz, I. Figueroa, L. Gonzalez, R. Lopez, M. Menendez, A. Bernardo, M. Reina, A. Sanchez, G. Garcia, A. Jimenez, M. Colombo, M. Canchal, J. Rodriguez
MTS (MIRI telescope simulator) is the Spanish contribution to the JWST Project. MTS is a part of the
Optical Ground Support Equipment (OGSE) for the Assembly Integration and Verification (AIV) and
Calibration phase of the MIRI instrument at the RAL (Rutherford Appleton Laboratory) facilities. Briefly,
MTS main objetive consists on delivering a diffraction-limited test beam, including the obscuration and
mask pattern, to the MIRI instrument that reproduces the output beam of the JWST in environmental
conditions similar to those corresponding to the flight.
In this work, the current status of the project is reported on. Mainly, after a description of the whole
instrument and the optomechanical performances required, the paper will be focused on the current status
of the purchase and characterization of certain critical elements belonging to the different subsystems.
The first step has been the verification of the thermoelastic behaviour of its structure, employing a
mass prototype. Both extensometer measurements and optical measurements with alignment mirror cubes
have been carried out during a thermal vacuum test of this MTS prototype. The correlation of the
measurements, optically and mechanically, will provide a better knowledge of the structure behavior and
will be used to define the integration process.
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