Baseline for extp Preliminary Design

Transcription

1 Baseline for extp Preliminary Design extp Mission Design Coordination Meeting IHEP, Beijing, March 2017

2 Overall configuration Instrumental performance requirements Mission performance requirements Budgets (mass, power & telemetry) Product trees Schedule 2

3 extp: enhanced X-ray Timing and Polarimetry Mission SFA & PFA LAD WFM Payload Configuration Optics Detectors Spectroscopic Focusing Array (SFA) 9 telescopes Nickel/SGO SDD Large Area Detector (LAD) 40 modules MCP collimator SDD Polarimetry Focusing Array (PFA) 4 telescopes Nickel GPD Wide Field Monitor (WFM) 6 cameras 1.5D coded mask SDD Gamma Ray Burst Monitor (GRM) (optional) 3 units - Scintillator 3

4 Exploded View of the Configuration Cameras LAD Optics for SFA & PFA LAD Assembly Module WFM Details of the spacecraft design in Dr. HONG Bin s talk. 4

5 Instrumental performance requirements Document: extp scientific requirements 0.9 5

6 Instrumental performance requirements 6

7 Instrumental performance requirements extp/pfa Energy range 2-10keV 2-10keV Effective area (4 PFAs) 400cm 500cm Energy resolution 1.8keV@6keV 1.5keV@6keV Field of view (FWHM) 8 arcmin (limited by detector size and focal lenght) 8 arcmin (limited by detector size and focal length) Angular resolution 30 arcsec (HPD) 15 arcsec(hpd) Point source localization Time resolution <500 μs <100 μs Dead time <10%@1Crab <3%@1Crab Background MDP (minimum detectable polarization) Maximum source flux (steady, peak) <3% <2% >0.5Crab, >5 Crab upto 24 houres >1Crab, >20 Crab upto 12 houres 7

8 Instrumental performance requirements 8

9 Mission performance requirements Orbit 550km, inclination <2.5 Pointing 3-axis stabilized, <36 arcsec (3σ) Measurement accuracy: <7 arcsec (3σ) Telemetry Steady: 1 Crab, peak: 10 Crab up to 24 hours Burst trigger time and location delivery to end user: < 30s Mission duration: 5 years (goal: 8years) 9

10 Interface to the platform Alignment Mirror assemblies of SFA & PFA: < 30 arcsec Focal plan assemblies of SFA & PFA Axial direction: < 1mm Lateral direction: < 0.5mm LAD modules: <1 arcmin WFM cameras: <30 arcmin, measurement: <15 arcsec Primary power supply: 42V High rate data link: SpaceWire H/K and TC: 1553B 10

11 Payload Block Diagram A preliminary scheme to show the baseline of power supply and data handling interfaces. 11

12 Major Changes and Impacts Baseline: SPIE paper, 2016 Optics: focal length, ~5.5m PFA: Nickel, focal length = 5.25m SFA: Nickel, focal length = 5.25m SGO, focal length ~5.5m Effective area increased ~8%@2keV, ~15@3keV, ~20%@6keV Mirror module mass budget increased ~25% Replace 2 spectroscopy cameras with polarimetry cameras Effective area for polarimetry: cm²@2keV 4~5x IXPE, for deeper polarimetric observations Effective area for spectroscopy: cm²@1keV Additional GRB monitor (GRM from SVOM) (optional) Energy range: 15~5000keV, area>200cm² Mass 36kg, power 35W 12

13 Payload Resource Budgets Mass (kg) Power (W) Data (Mbps) (Tb/day) Uncompressed compressed SFA(9) LAD (incl. support structure) PFA(4) WFM(incl. support structure) Thermal control Total % margin Assumption: 80% sky visibility (for the telemetry requirement estimation) Onboard mass memory allows observation of sources up to 10 Crab intensity for up to 24 hours. 13

14 Mass and Power Budgets instrument SFA PFA subsystem SFA 聚集镜组件,SFA Mirror Assembly SFA 焦平面组件,SFA Focal Plan Assembly in diameter 20± SDD:-100~-80, stability ±0.5 电控箱,DHU-F ~+45 配电箱,PCDU total PFA 聚集镜组件,PFA Mirror Assembly PFA 焦平面组件,PFA Focal Plan Assembly nb. Of unit single unit mass (kg) total mass(kg) total mass with 20% margin (kg) single unit power (W) total power (W) total power with 20% margin (W) in diameter 20± GPD:25±1, case 10±3(TBC) 电控箱,DHU-F ~+45 total LAD module *345*66-20~-10 Panel structure envlope (mm) working temperature ( ) LAD WFM - Panel Radiator PBEE *400*300-10~+45 harness(module->pbee) ICU LAD deployable structure (incl. sunshade) total WFM module *345* ~-22 ICU(2) ~+50 harness(camera->icu) Support sturcture deployable structure total power supply and thermal controller Total

15 Data download Baseline: X-band Telemetry Sanya(18N, 109E): 12m, 600~900Mbps Malindi(3S, 40E): 13m (2018) India (TBD): Bangalore(13N, 77E), Thiruvananthapuram(8N,77E) Alternative: Ka-band (2250Mbps) Shared with the relay satellite communication system Sanya ground station: antenna can be upgraded to Ka-band Burst Alert system VHF transmitter Short message, BeiDou Navigation Satellite System 15

16 Model philosophy (instrument/equipment level) ECSS-E-HB-10-02A DM: Development Model or Demonstration Model 原理样机 SM: Structural Model 结构件 STM: Structural Thermal Model 结构热控件 EFM: Electrical and Functional Model 电性件 QM: Qualification Model 鉴定件 FM: Flight Model 正样 FS: Flight Spare model 正样备份件 16

17 Payload equipment requirements STM Deliverable EFM Deliverable QM Non-deliverable FM Deliverable FS Deliverable as required SFA mirror assembly (SFM) PFA mirror assembly (PFM) SFA camera assembly (SFC) 9 1(TBC) PFA camera assembly (PFC) 4 1(TBC) SFA ICU 3 3(TBC) PFA ICU PCDU 1 1(TBC) LAD module 40 4(TBC) LAD PBEE 4 4(TBC) LAD ICU 1 1(TBC) WFM Camera 6 1(TBC) WFM ICU 1 1(TBC)

18 Product tree of SFA Level-0 Spectroscopy Focusing Array (SFA) Level-1 Focusing Mirror Assembly (SFM) Focal Plan Camera (SFC) Instrument Control Unit (ICU-S) Level-2 Mirror module baffle Electron deflector Focal Plan Assembly Filter Wheel Assembly Level-3 SDD Detector Focal Plan Electronics Structure Level-4 SDD array DAQ Filter Wheel Stepper Motor Pre-amplifier Power Supply Baffle Structure IHEP Passive shield Software Filter Films MPE Thermal control Calibration Source 18

19 Product tree of LAD 19

20 Product tree of PFA 20

21 Product tree of WFM 21

22 extp System Product Tree with Main Responsibilities extp Mission Space Segment Launch Segment Telemetry and Control Segment Operational Ground Segment Science Ground Segment Spacescraft LM-7 Mission Operations Center Science Operations Center Sanya Ground Station Science Data Center Payload Support Service Module (SVM) Payload Malindi Ground Station European science data center Mirror support platform LAD Deployment mechanisms SFA LAD PFA WFM Burst Alert Ground Segment Focal plan support platform Telescope tube LAD Sunshields WFM Deployment mechanisms SFA mirror assemblies SFA focal plan cameras LAD modules PBEE PFA mirror assemblies PFA focal plan cameras WFM camera WFM ICU Short message service of BeiDou Navigation satellite system Telescope cover Venting mechanism WFM support structure Thermal control SFA ICU LAD ICU Harness PBEE modules PFA ICU WFM harness camera ICU VHF antennas Focal plane radiator Panel structure incl. radiator Focal plane sunshield China Europe 22

23 Schedule Phase A2: ~ , international coordination, feasibility design ~ , Subsystem interface definition document (IDS) ~ , Subsystem requirements document ~ , System feasibility design Phase B: ~ , Preliminary design ~ , Subsystem preliminary design ~ , System preliminary design Phase C: ~ , System critical design ~ SM delivery(30% for special test(tbd)) ~ EFM delivery ~ STM delivery ~ QM completed Phase D: ~ , Flight model and launch ~ FM delivery Launch 23

24 Thanks 24