Il programma NHXM sviluppato dall'ASI Ing. Mauro Piermaria

1. Il programma NHXM sviluppato dall'ASI Ing. Mauro Piermaria New Hard X-Ray Mission Workshop Nazionale 12 e 13 novembre 2009 – ASDC, Frascati

2. PRESENTATION TOPICS • DEVELOPMENTS OF THE ASI NHXM PROGRAM • NHXM PHASE A: THE PEOPLE • NHXM PHASE A: PRODUCT TREE • NHXM PHASE A: INDUSTRIAL ORGANISATION • NHXM PHASE A: DETAILED ACTIVITIES • NHXM PHASE A: THE COMMON PLATFORM • SIMBOL-X MAIN CARACHTERISTICS • EXIT-SAT: MAIN SPECIFICATIONS • EXIT-SAT: CONFIGURATION • CONCLUSIONS

3. DEVELOPMENTS OF THE ASI NHXM PROGRAM • NHXM is the ASI program with the aim to launch a new mission for Hard X-ray observations • Pre-phase A study, in the NHXM frame, mainly relevant to the Simbol-X collaboration has been conducted; 9/2006 – 1/2007. • NHXM phase A contract with Mirror technological development, MSC satellite of Simbol-X development and Exit-Sat Satellite development started in 7/2007. • First change with deeper analysis on mirror technology (Ni-Co electroforming, Multilayer deposition) • Second change with the development of a common platform for MSC and DSC (to be used also for EXIT-SAT) • Conclusion of the NHXM phase A (Simbol-X and Exit-Sat phase A), 1/2009. Initial duration of 13 months, extended to 18 months. • A further technological study (only on X-rays multilayer mirrors), continuation of the work performed during the NHXM phase A, has been initiated in 3/2009, and still on going.

4. NHXM PHASE A: THE PEOPLE • Continuous collaboration with CNES on Simbol-X program, while only Italian involvement on EXIT-SAT mission. • Continuous improvement of the knowledge by confrontation with our program partners • Conclusion of the ASI-CNES collaboration on Simbol-X Program, 4/2009. • Internal Agency resources (8+1 persons). • INAF resources (from different locations and institute) • Industrial resources (TAS-I, MLT, BCV, TPZ, INAF-OAB) • Large but efficient integrated team working on NHXM for almost 2 years. • Once again, demonstrated ability for such a team, to deal and interact productively with other international partners.

5. NHXM PHASE A: PRODUCT TREE

6. NHXM PHASE A: INDUSTRIAL ORGANISATION ASI TAS- I (ex AAS- I) Prime

7. SIMBOL X- MSC SVM Design definition I/F Design definition (MSC- DSC and MSC - Soyuz) Mechanical and Thermal Models Ground Segment network structure and functions implementation Operations Strategy Implementation Frozen Final Mission Architecture Model Philosophy definition Engineering Support to ASI (JPO) Cost evaluation NHXM PHASE A: DETAILED ACTIVITIES MIRROR MODULE • Materials and process optimization • MM engineering • Mirror shells electroforming and replication • MM scientific liaison • Design T/M analysis • Structural design & analysis • Prototypes production and delivery of Mandrels and multilayered sample shells • Technology Assessment HEXITSAT • Preliminary HexitSat Design • Ground Segment preliminary implementation • Mission architecture Operations Strategy Implementation • HXMT Compatibility evaluation

8. NHXM PHASE A: THE COMMON PLATFORM DSC HEXITSAT HXMT SIMBOL-X MSC

9. Field-of-View 12 arcmin Absolute pointing 20 arcsec Mirror Satellite Line-of-Sight Reconstruction 4.7 arcsec 20 m Detector Satellite +/-1 cm SIMBOL-X MAIN CARACHTERISTICS Concept: • high-energy new generation telescope, spectral range from classical X-rays to hard X-rays (0.5-80 keV); 2 orders of magnitude better in sensibility and spatial resolution. • Long focal length using Formation Flying. • Mirror and Detector mounted on two different spacecrafts in Formation Flying. • High elliptical orbit (20.000-180.000 km) Optics: • Shells mechanics from of Italian know how • Reflecting material: multilayer to increase the field of view and the spectral bandwidth Focal plane: • Passive collimator with active anticoincidence • Two superposed spectro-imager (Low Energy 0.5–20 keV; High Energy CdTe 15–100 keV)

10. EXIT-SAT: MAIN SPECIFICATIONS • Four Mirror modules (12 mirror each), multilayer optics. • Four detectors, each aligned with the corresponding mirror • Focal distance 8-10m (deployable truss) • 1000-1500Kg /600 W Satellite class • Near circular equatorial orbit, 600 Km altitude (Beppo-sax like). • Utilisation of the Malindi Station

11. EXIT-SAT: CONFIGURATION Focal Plane Assembly Deployable Truss Folded configuration, in the VEGA Launcher fairing Solar Array Service Module

12. CONCLUSIONS • During the last period, ASI made big efforts to pursue the NHXM Program (financial and HR). • We envisaged a broad involvement by the Italian community, either scientific and industrial. • The Simbol-X project, and the collaboration with the French partners, unfortunately stopped, brought a lot of experience on this kind of mission, for both scientific and engineering issues. • Feasibility of Exit-Sat and Simbol-X missions at the end of the projects phase A has been proved. By the way, some Items of Exit-Sat mission need to be further investigated. • ASI (and the collaboration network) has availability of know how, results and documentation on the above mentioned projects.