ESA Science & Technology - Publication Archive
This document has been prepared to give a concise overview of the studies that have been performed in the framework of the Jovian related Technology Reference Studies. The goal of these studies is the identification of technologies that are required to enable possible low resource missions to the Jovian System. These activities are subdivided in three main topics:
- The Jovian Minisat Explorer (JME): The exploration of Europa and the Jovian System
- The Jupiter Entry Probe (JEP): In situ exploration of the Jovian atmosphere up to 100 bar
- The Jovian System Explorer (JSE): Study of the Jovian magnetosphere and the Jovian System
The purpose of this preliminary payload resources document is to translate the typical science requirements into a payload resource budget, which is required for the first part of the system design of the Cross-scale TRS.
The document is (currently) an open document and regular updates, primarily refinements, are expected. Particularly, iterative steps with industrial study partners and the ESA TRS study manager are foreseen. Revisions will be published, as required, at the start of as well as during the system design. This document will be evolved into a straw man Payload Definition Document.
The purpose of the mission requirements document is to provide level 1 (mission) requirements for the Cross-scale TRS system design study.
- Formation and evolution of stars
- Formation of planetary systems and planet detection
- Formation and evolution of galaxies
- To assess the feasibility of a far-infrared Michelson interferometer based on a single spacecraft
- To design the mission
- To identify the critical technologies and define their development plan
- To make cost, risk and programmatics analysis for the mission and for the technology development plan
- a Phase 1 devoted to requirements review and architecture trade-of: it has led to the selection of the non planar arrangement
- a Phase 2 devoted to preliminary design: together with the consolidation of the selected arrangement, it has produced the payload and spacecraft preliminary design, including performance budgets
In addition, the scientific community requirements are more and more challenging: demanding mission objectives lead to more complex mission concepts. Moreover, a quicker response time from approval to launch would be desirable, whilst keeping a very high overall level of reliability.
The main objective of this study is to review the application of recurring service modules as a potential answer to the challenges listed above.
The ESA Concurrent Design Facility (CDF) was requested and financed by ESA/ESTEC/SCIAM to carry out a feasibility study for an optical-near-infrared wide field imager (WFI). Such a mission would search for Type Ia supernovae over a given redshift range with optical and near infrared wavelength coverage. The overall aim of the mission would be to use supernova observations to model the changing rate of expansion of the universe and to determine the contributions of decelerating and accelerating energies such as the mass density and dark energy density. This model could be constructed using a Hubble diagram (redshift vs. magnitude) populated with supernovae measurements. This study is the first step in the feasibility assessment of a technology reference mission and a follow-on phase-A industrial study is foreseen for the payload, where most of the technology development is needed.
Chronology is the key to understanding climatically and tectonically driven changes on Mars. The objective of the present proposal was to assess the potential of in-situ Martian sediment dating using luminescence techniques. The work was divided into two parts:
- a) Work package 1 : Review and optimisation of appropriate techniques and instrumentation
b) Work package 2 : Laboratory measurements and proposals for instrumentation.
The aim of the activity was to develop and test an Instrumented Mole System (IMS) - i.e. a system able to deploy a mobile penetrometer carrying a payload of sensors for sub-surface measurements - to be mounted on a Planetary Lander.
This IMS could potentially be used on future planetary missions such as those for the exploration of the surface of Mercury or on other planets.
A summary of the study evolution has been provided in the previous XRO status report [RSStRep] issued at the end of March 2006. The work of ESA and JAXA on the revised mission scenario has progressed further over the past 6 months, including internal as well as industrial activities and dedicated technology developments.
In response to ESA's call for space science themes in the frame of Cosmic Vision 2015-2025, the scientific community identified a Far Infrared mission with very high spatial resolution as a potential future science mission for Europe. A future far infrared mission would typically work at wavelengths between 25-300 microns and combine high sensitivity with an angular resolution better than 1 arcsecond at the shortest wavelengths. Such requirements would call for very large telescope diameters or for an interferometer based design.
To investigate the feasibility of this potential future mission the Science Payload & Advanced Concepts Office (SCI-A) at ESA initiated a Far Infrared Interferometer (FIRI) Technology Reference Study (TRS). The selected baseline concept for this study is a single spacecraft Michelson interferometer (i.e. pupil plane recombination) with two light collecting telescopes and a central hub beam combiner, all cryogenically cooled. To enable such a mission concept many innovative design solutions and technology developments would be required in the area of cryogenics, mechanisms and optics.
In this paper an overview of the result of the internal feasibility study of the FIRI concept will be provided. Specific emphasis is on critical subsystems and on required future technology development activities.
In response to ESA's call for space science themes in the frame of Cosmic Vision 2015-2025, the scientific community identified a Wide-Field Optical and Near Infrared Imager as a potential future science mission for Europe. Such a mission would search for Type Ia supernovae at low redshift in the optical and near infrared part of the spectrum with the aim to measure the changing rate of expansion of the universe and to determine the contributions of decelerating and accelerating energies such as the mass density, the vacuum energy density and other yet to be studied dark energies. To investigate the feasibility of this potential future mission the Science Payload & Advanced Concepts Office (SCI-A) at ESA initiated the Wide Field Imager (WFI) Technology Reference Study (TRS). The WFI would have a 2 m class telescope, a 1 square degree field of view imaging camera and a low-resolution integral field spectrometer. This paper summarizes the results of this ESA internal feasibility study of the WFI. The paper focuses on the spacecraft design and the critical subsystems and provides an overview of required technology development activities for such a mission.
This paper summarizes the results of an ESA feasibility study of a Wide-Field Optical Infrared Imager (WFI) that would search for Type Ia supernovae at low redshift with the aim to measure the changing rate of expansion of the universe. WFI multi-spectral images of the deep universe could also benefit to many other research area in astrophysics. The WFI payload includes a 2 m class telescope, a 1 square degree field of view imaging camera and a low-resolution integral field spectrometer. A mission concept was identified that consists of a 2000 kg spacecraft launched by a Soyuz-Fregat into a L2 halo orbit. The WFI mission could benefit from the technology developed for the ESA Herschel and Gaia missions and for the NIRSpec ESA instrument. A fully European WFI mission would require improvement of existing European detector and on-board processor technology as well as some effort to support the utilization of the 26 GHz Ka band.