Development of

a

Thomson X-ray Polarimeter for a Small Satellite Mission Rishin P.V., Gopala Krishna M.R., Biswajit Paul, Duraichelvan R., Chandreyee Maitra, Ateequlla C.M., Rajagopala G., Ezhilarasi M.S., Sandhya P., Mamatha T.S., Nagaraja H.N.

Raman Research Institute, Bangalore, India Abstract

We describe development of a Thomson X-ray polarimeter for a small satellite mission of the Indian Space Research Organisation (ISRO). A laboratory model was made and tested successfully and it was redesigned for a flight unit.

Fabrication of an engineering model is in final stages. The instrument consists of position sensitive proportional counter detectors and works in the 5-30 keV energy band. This instrument will be suitable for X-ray polarisation measurement in about 50 hard X-ray sources. The accretion powered X-ray pulsars, black hole X-ray binaries, rotation powered pulsars and non-thermal SNR will be the prime targets for this mission. In spite of its moderate sensitivity, this experiment can give us unique opportunity to expand the field of X-ray astronomy into a hitherto unexplored dimension. This instrument will complement the hard X-ray polarisation measurements to be obtained with Compton polarimeters and allow study of polarisation characteristics of X-ray sources over a wide energy band. We describe the mission specifications, its sensitivity, the mechanical and electronic design aspects of the complete system, the signal processing pipe-line and test results.

Instrument Configuration

Figure shows the configuration of the Thomson Polarimeter. Here the detector elements are flat multi-wire proportional counters placed on four sides of a disk-like scattering element made of Be or Li. The geometry of the scatterer is optimized using Geant4 simulation to get highest sensitivity 6 .

We are using position sensitive proportional counters employing 12 nos. of resistive Nichrome wires split into two channels. This helps to improve the modulation factor and achieve better background rejection at the edges of the detector. The position sensitivity is achieved by charge division method as shown in figure. The processing electronics logic is implemented in

Field Programmable Gate Array (FPGA) .

Fabricated Engineering Model Detector Introduction

The space X-ray astronomy experiments carried out during the last three decades have brought a few order of magnitude improvement in sensitivity for Timing, Spectroscopy and Imaging. However, in the whole history of X ray astronomy, the Crab Nebula is the only X-ray source for which definite polarisation measurements exist 1 . Some key scientific issues in high energy astrophysics require input from polarisation measurement 2,3,4 . Hence there is a strong need for X-ray polarisation measurement.

A Thomson polarimeter working in the energy band 5-30 keV is being developed at Raman Research Institute (RRI) 5 . A laboratory model has been made and tested successfully, an engineering model has been designed and fabrication of the same is in progress.

The instrument has been proposed for an independent small satellite mission of the Indian Space Research Organisation (ISRO).

Principle of Operation

The instrument is based on

anisotropic Thomson scattering

of X-ray photons.

X-rays from the source are made to undergo Thomson scattering and the intensity distribution of the scattered photons is measured as a function of azimuthal angle. Polarised X-ray will produce an azimuthal modulation in the count rate. The total configuration will be rotated about the viewing axis.

Mechanical analysis

Finite Element Analysis (FEA)

based on the has been carried out on the above design

Environmental Test Level Specifications (ETLS)

specified by the

Indian Space Research Organization (ISRO) of the small satellite platform

to parametrically optimize the design for minimum mass and maximum stiffness. The natural frequency of the structure and the maximum stress/displacement developed in the model meets the qualification model requirements with ample factor of safety.

Fabricated Prototype Collimator

In order to to compensate for inaccuracy in satellite pointing and to attain constant effective area, a collimator with a flat topped response is required. For the Engineering model, we plan to use solid aluminum block with hexagonal tapered holes, machined using wire-cutting technology to achieve a flat topped response. Figure shows both faces of the sample piece machined for the engineering model collimator.

Signal Processing Electronics

FE Front-end electronics PE Processing electronics

Results

One of the engineering model detectors has been fabricated and tested.

Figure shows the position determination by charge division for this detector when shined with radioactive source. Peaks in the figure show the position of the radioactive source when shined on the detector.

Instrument Specifications

The table below describes the specifications of the Thomson X-ray polarimeter. This instrument will complement the Hard X-ray polarisation measurements to be obtained with Compton polarimeters and allow study of polarisation characteristics of X-ray sources over a wide energy band.

Description

Photon collection area Energy range Field of view Detectors Total weight Overall dimension Power Data generation rate Scattering element Life time Modulation factor Sensitivity Satellite requirements

Value

1018 cm 2 5-30 keV 3



3 degree with ± 0.2 degree flat topped response Proportional counters ~100 kgs.

~ 650 x 650 x 550 mm 3 50 Watt 4.2 Gbits per day Beryllium/Lithium 3-5 years ~40% 2-3%

M

inimum

D

etectable

P

olarisation (

MDP

) for 50 mCrab sources with 1 mega sec exposure Equatorial orbit (preferred) of altitude 500-600km, with pointing accuracy of 0.1 deg, and with spin along roll axis of about 0.5 rpm

Polarimeter electronics block diagram

Future Plans

Integration of one engineering model detector and testing with the signal processing electronics chain is successfully completed.

Position determination using charge division principle is demonstrated. Work towards fabricating the remaining detectors along with signal processing electronics is in progress.

References

[1] M. C.Weisskopf et al., “Measurement of the X-ray Polarisation of the Nebula”, ApJ, 208, L125-L128 (1976) [2] M. C.Weisskopf et al.,“The prospects for X-ray polarimetry and its potential use for understanding neutron stars”, astro-ph/0611483, (2006) [3] Kallman T., “Astrophysical motivation for X-ray polarimetry”, Advances in Space Research 34, 2673-2677 (2004) [4] Chandreyee Maitra et al., “ Prospect of polarisation measurements from black hole binaries in their thermal state with a scattering polarimeter”, arXiv:1103.2639 [astro-ph.HE], (2011) [5] Rishin, P.V. et al., “ Development of a Thomson X-ray Polarimeter”, arXiv:1009.0846v1

[astro-ph.IM], (2009) [6] Vadawale et al., “Comparative study of different scattering geometries for the proposed Indian X-ray polarization measurement experiment using Geant4”, Nuclear Instruments and Methods in Physics Research - A, 618, 182, arXiv:1003.0519v1,(2010)

Acknowledgement

We would like to thank Dhiraj Dedhia (TIFR), Parag Shaw (TIFR), Vadawale S.V. (PRL), Cowsik R. (Washington University, USA), and Seetha S (ISAC, ISRO) for all the timely help and support. Special thanks to the members of RRI Mechanical Engineering Services.

For details contact : rishinpv/gkrishna/[email protected]