XEUS: Payload Accommodation with the Detector Spacecraft
- Paper number
IAC-06-A3.1.07
- Author
Ms. Kelly Geelen, Astrium Ltd., United Kingdom
- Coauthor
Mrs. Marie-Claire Perkinson, EADS Astrium Ltd., United Kingdom
- Coauthor
Dr. Paolo D Arrigo, EADS Astrium Ltd., United Kingdom
- Coauthor
Ms. Elizabeth Seward, EADS Astrium Ltd., United Kingdom
- Year
2006
- Abstract
XEUS is under consideration by ESA for its Cosmic Vision programme that consists of a series of advanced missions following-on from ESA successes such as XMM-Newton. The design, development and operation of a state-of-the art X-ray payload of the size and complexity of XEUS represent a tremendous technical, programmatic and financial challenge. The XEUS Instrument Accommodation Study is the first step towards the realisation of this scientifically rewarding mission. The current baseline design for XEUS requires novel X-ray optics with a focal length of 35m. Achieving this focal length requires two spacecraft flying in formation. One spacecraft is designated the Mirror Spacecraft (MSC) and the other, containing the instruments, the Detector Spacecraft (DSC). The spacecraft pair will observe target stars whilst flying in formation at L2, pointing close to 90 degrees from the Sun direction. The purpose of the current industrial activity is to assess the accommodation options and the resources required by the instruments. The core instruments have been defined, together with a set of auxiliary instruments which can be added if resources allow. The core payload consists of a Wide Field Imager (WFI) and a Narrow Field Imager (NFI). Currently, there are two possible designs for the NFI, namely a detector based on Transition Edge Sensor (TES) technology or one using Superconducting Tunnel Junction (STJ) technology. Both types of detectors have differing requirements with respect to accommodation and both are considered in the study. The ancillary instruments are a High Time Resolution Spectrometer (HTRS), a Hard X-ray Camera (HXC), and an X-ray Polarimeter (XPOL). There are numerous challenges for the implementation of the instruments which include very low operating temperatures (30-300mK), control of magnetic fields at instrument level, stringent contamination requirements, shielding and baffling against straylight and particles incident on the open detector apertures, and the integration of all the instruments with the spacecraft. This paper will present the critical issues and design drivers for payload accommodation within the detector spacecraft together with possible solutions.
- Abstract document
- Manuscript document
IAC-06-A3.1.07.pdf (🔒 authorized access only).
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