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Esa Standard Document Technology Reference Study Final Report GRL The Gamma Ray Lens SCI-A/2005.058/GRL/CB Craig Brown July 2005 s Page 1 of 172 T ECHNOLOGY R EFERENCE S TUDIES The Science Payload and Advanced Concepts Office (SCI-A) at the European Space Agency (ESA) conducts Technology Reference Studies (TRSs), hypothetical science driven missions that are not currently part of the ESA science programme. Most science missions are in many ways very challenging from a technology point of view. It is critical that these technologies are identified as early as possible in order to ensure their development in a timely manner, as well as allowing the feasibility of a mission to be determined. Technology reference studies are used as a means to identify such technology developments. The Technology Reference Study begins by establishing a series of preliminary scientific requirements. From these requirements, a hypothetical mission is designed that is capable of achieving the scientific goals. Critical issues and mission drivers are identified from the new mission concept and, from these drivers, a series of technology development activities are recommended. One such TRS has been conducted on a Gamma Ray Lens (GRL) mission. The GRL is an ideal candidate for a TRS due to the challenging nature of the technologies involved with focusing gamma rays. Identifying the key areas requiring technology development in this field prepares for any future high-energy astrophysics mission that the science community may propose, as well as establishes common technology development requirements possibly shared by different science missions. s page 2 of 172 A BSTRACT This is the final report for the Gamma Ray Lens (GRL) technology reference study performed by SCI-AM. The Gamma Ray Lens concept arrises in response to the desire for high-energy observations of increased sensitivity in the soft gamma-ray regime. Part one of this report is concerned with the theoretical aspects of the gamma ray lens. In particular, this section establishes a reference science case and science requirements for the GRL, as well as outlines the theory of multilayer mirrors and Laue crystals – the two technologies considered for gamma ray focusing in this report. Focal plane instrumentation is also investigated, with possible GRL detectors introduced and discussed. Finally, a sensitivity analysis model is introduced, used in part two as a tool to investgate potential GRL Laue lens configurations. Part two contains the detail relating to the GRL mission design. This section outlines two Gamma Ray Lens profiles that were investigated for the TRS; a smaller Soyuz Fregat spacecraft and a larger Ariane 5 scenario. Effective area profiles and sensitivity analyses were conducted for both configurations, technology drivers were derived, and conclusions were made based on the science requirements outlined in part one. It was found that the smaller Soyuz Fregat configuration, although achieveing two orders of magnitude improvement on the sensitivity of SPI-INTEGRAL, was not capable of achieving all of the science requirements set out in part one. The Soyuz configuration failed to observe all energy bands of interest due to the mass constraints of the launcher. The complexity of two separate launches for the GRL optic and detector spacecraft, also make the smaller configuration undesirable. The Ariane 5 configuration achieved all of the science requirements introduced in part one. A third Extended Ariane 5 lens configuration also demonstrated further potential by greatly increasing the energy band of the instrument. For this reason, the Ariane 5 configuration was chosen as the GRL mission baseline. From the conclusions of the mission design, a series of future actions and potential technology development activities (TDA) were identified. 2 s page 3 of 172 T ABLE O F C ONTENTS 1. Introduction 9 Part I – Theoretical Aspects of the Gamma Ray Lens Mission 2. A Reference Science Case for the Gamma Ray Lens 11 2.1 Sources of interest in the Soft Gamma Ray regime 11 2.2 Preliminary Science Requirements Applicable to the GRL 16 2.3 The INTEGRAL Mission 18 2.4 References 25 3. High Energy Focusing Technologies 27 3.1 Graded Multilayer Mirrors 27 3.1.1 Hard X-ray and Soft Gamma Ray Astronomy 27 3.1.2 Principles of Multilayer Mirrors 28 3.1.3 Optic Design 32 3.1.4 Conclusions 36 3.1.5 References 37 3.2 Laue Crystals 38 3.2.1 Laue Diffraction 38 3.2.2 Direction of Diffraction 38 3.2.3 Throughput of the Diffracted Ray 39 3 s page 4 of 172 3.2.4 Mosaicity 40 3.2.5 Temperature Effects 42 3.2.6 Gradient Crystals 43 3.3 The Basic Laue Lens Principle 44 3.3.1 The Focal Spot 45 3.3.2 Effective Area of the Gamma Ray Lens 46 3.3.3 Lens Size and Deployable Optics 48 3.3.4 References 49 4. Focal Plane Instrumentation and Technologies 50 4.1 Gamma Ray Interaction with Matter 50 4.1.1 Photoelectric Absorption 50 4.1.2 Compton Scattering 51 4.1.3 Pair Production 52 4.2 High Energy Photon Detectors 53 4.2.1 Germanium Detectors 53 4.2.2 Scintillator Detectors 54 4.2.3 Compton Detectors 57 4.2.4 Polarisation Detectors 59 4.3 The Miniature 50-80 K Pulse Tube Cooler 60 4.4 References 61 4 s page 5 of 172 5. Sensitivity Analysis 62 5.1 Input to the Model 62 5.2 Model Description 63 5.3 Model Output 65 5.4 Results 66 5.5 References 66 Part II – Gamma Ray Lens Mission Design 6. Other Missions Useful to the GRL Design 68 6.1 Claire and MAX 68 6.1.1 Claire 68 6.1.2 MAX 72 6.1.3 Conclusions 76 6.1.4 References 77 6.2 XEUS 78 6.2.1 The XEUS Mission 78 6.2.2 Gamma Ray Lens: XEUS Similarities 82 6.2.3 Conclusions 83 6.2.4 References 83 5 s page 6 of 172 7. Orbit Selection 84 7.1 Orbit Type and Trade-off 84 7.2 L2 Orbit Type 86 7.2.1 Lissajous Orbits 86 7.2.2 Halo Orbits 87 7.3 Orbit Selection Conclusions 89 7.4 References 90 8. Mission Profile 1 – Soyuz Fregat 91 8.1 Orbit Insertion 91 8.1.1 Direct Insertion 91 8.1.2 L2 Insertion via Highly Elliptical Transfer Orbit 91 8.1.3 Launch Windows 92 8.1.4 Launch Profile Conclusions 93 8.2 Optics Spacecraft (OSC) 94 8.2.1 Payload 94 8.2.2 Subsystems 94 8.2.3 System Budgets 97 8.3 Detector Spacecraft (DSC) 99 8.3.1 Payload 99 8.3.2 Subsystems 100 8.3.3 System Budgets 101 6 s page 7 of 172 8.4 Mission Configuration 102 8.4.1 Effective Area 103 8.4.2 Sensitivity Analysis 104 8.5 Soyuz Fregat Mission Profile Conclusions 105 8.6 References 106 9. Mission Profile 2 – Ariane 5 107 9.1 Single Launch Mission Analysis 107 9.1.1 Direct Launch 107 9.1.2 HEO Launch 107 9.1.3 Launch Profile Conclusions 108 9.2 GRL Optics Spacecraft (OSC) 109 9.2.1 OSC Configuration 109 9.2.2 Payload 112 9.2.3 Subsystems 115 9.2.4 Mass Budget 117 9.2.5 Power Budget 119 9.3 GRL Detector Spacecraft 120 9.3.1 DSC Configuration 120 9.3.2 Payload 123 9.3.3 Subsystems 125 9.3.4 Mass Budget 125 9.3.5 Power budget 126 7 s page 8 of 172 9.4 GRL Mission Configuration 127 9.4.1 Mission Architecture 127 9.4.2 Link Budget and Ground Segment 131 9.4.3 Laue Lens Effective Area 134 9.4.4 Sensitivity Analysis 135 9.5 Ariane 5 Mission Profile Discussion 136 9.6 Ariane 5 Mission Profile Conclusions 141 9.7 References 141 10. Future Work and Potential Technology Development Activities 142 10.1 Future Activities 142 10.2 Technology Development Activities 144 10.3 References 146 11. Appendices 147 11.1 Appendix A - Soyuz Launchers; Current Status and 147 Proposed Upgrades for use to L2 11.2 Appendix B - Point Spread Function Size – Derivation 152 11.3 Appendix C - Structural Requirements for the Gamma Ray Lens 155 11.4 Appendix D – XEUS Mission and MSC Design 160 11.5 Appendix E – Ariane 5 GRL Systems Mass Budget 163 11.6 Appendix F - Margin Philosophy for Assesment Studies 166 8 s page 9 of 172 1. Introduction The Science Payloads and Advanced Concepts Office has introduced the idea of performing Technology Reference Studies (TRS) in order to recognise and encourage the development of new technology concepts for possible future scientific missions. There are four primary areas of investigation in the TRS programme; Planetary, Solar, Astrophysics and Fundamental physics missions. As part of the Astrophysics missions theme, it has been decided to include the preliminary study of a gamma ray focuser. This study will aim to establish the advances in instrumentation required to make such a mission viable in the future. The progression of gamma ray astronomy relies on the development of higher sensitivity instrumentation. Current technologies utilised in the field operate in the background-limited regime and have thus reached a critical point in their development. Any further increase in instrument sensitivity requires an unreasonable increase in spacecraft mass, resulting effectively in unviable space missions. This suggests the need to develop a gamma ray focuser – an optic capable of concentrating gamma rays onto a small detector, thus minimising background and maximising sensitivity. This report will detail the scientific justification of such a mission, describing the potential return from the use of a ‘Gamma-Ray Lens’.
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