1. Sun Earth Connection Coronal and Heliospheric Investigation STEREO and SECCHI Status Consortium Meeting, Abingdon 11-12 July 2001 Russ Howard

2. Sun Earth Connection Coronal and Heliospheric Investigation Outline STEREO Mission Status Spacecraft Status SECCHI Program Status SECCHI Technical Status Upcoming meetings

3. Sun Earth Connection Coronal and Heliospheric Investigation STEREO Mission Status (1) NASA HQ approved the STEREO development plan at a Pre-confirmation Review on 20 May 2001 This approval turned out to be more difficult than thought, requiring the project to go through a number of program planning exercises The primary difficulties were –Insufficient funding in 2000, 2001 and 2002 –Increased program reviews due to recent failures The funding shortage resulted in Phases A & B being stretched – Phase B goes until March 2002

4. Sun Earth Connection Coronal and Heliospheric Investigation STEREO Mission Status (2) Design Reviews Delayed –SECCHI PDR on 26, 27 September 2001 (from May) –Spacecraft PDR in December 2001 –CDR about October, November 2002 A significant problem was that the perceived program risk did not match the funding schedule or the development schedule. By delaying launch until November, 2005, these problems were solved

5. Sun Earth Connection Coronal and Heliospheric Investigation STEREO Spacecraft Names Naming contest resulted in very inventive pairs –Comedic: A Dollar Late and A Day Short –Mythology Figures: Osiris and Isis –Audio References: AM and FM Ahead (A) and Behind (B) were chosen

6. Sun Earth Connection Coronal and Heliospheric Investigation Spacecraft Status Mission design is indicating that there is an interesting lunar eclipse possibility during phasing orbits Telemetry rates as a function of mission phase New configuration is being proposed (approval within days if not already) Beacon mode is being planned for, but NASA is looking for partners to contribute their ground stations to acquire the data.

7. Sun Earth Connection Coronal and Heliospheric Investigation MISSION DESIGN

8. Sun Earth Connection Coronal and Heliospheric Investigation STEREO Mission Design Place two identical spacecraft in heliocentric orbits: One spacecraft leading the Earth (AHEAD), One spacecraft lagging the Earth (BEHIND). Use lunar flybys to impart a mean drift rate relative to the Earth: AHEAD spacecraft +22 degrees/year BEHIND spacecraft –22 degrees/year Minimize the eccentricity of the heliocentric orbits in order to minimize variation in apparent diameter of the Sun. Launch: November, 2005.

9. Sun Earth Connection Coronal and Heliospheric Investigation

10. Mission Orbit Extrema Nominal distances computed for the November 2001 launch date.

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15. Calibration and PR Opportunity During Phasing Orbits

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19. Telemetry Rates at Various Mission Phases

20. Sun Earth Connection Coronal and Heliospheric Investigation Downlink Data Rates Data rates are a function of distance of spacecraft from earth 354 to 500 kbps early in mission phase (TBC) 354.0 kbps - science data rate for 2 year mission 177.0 kbps - extended mission and S/C checkout 88.5 kbps - extended mission and S/C checkout 29.5 kbps - extended mission 1.2 kbps - extended mission,  -V burns and flybys 11 bps - emergency acquisition mode

21. Sun Earth Connection Coronal and Heliospheric Investigation Extended Mission Telemetry Rate AHEAD Spacecraft

22. Sun Earth Connection Coronal and Heliospheric Investigation Extended Mission Telemetry Rate BEHIND Spacecraft

23. Sun Earth Connection Coronal and Heliospheric Investigation Telemetry Rates Problem There may be a problem with the downlink rates. APL had been working to give us a rate that was 2x the nominal rate. This would have enabled 2x the volume per day early in the mission for the same amount of DSN contact time. However the frequency spectrum managers may not be giving the STEREO program sufficient band-width to enable the 2x, nor some of the other telemetry rates in the later phases of the mission.

24. Sun Earth Connection Coronal and Heliospheric Investigation New Spacecraft Configuration

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26. Spacecraft Configuration Modifications Modified center structure to meet ascent phase stiffness requirements Shortened observatory height from 66 to 61 inches –Results in increase of max launch mass from 1219 to 1255 kg SECCHI electronics box split into two and moved internally Baseline concept was over constrained on “SECCHI” panel (-Z) in both volume and mass New baseline virtually approved, but location of SWAVES and some of the IMPACT sensors still being worked –NOTE: SWAVES booms are moving in the HI field of view

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29. Note

30. Sun Earth Connection Coronal and Heliospheric Investigation Note

31. Sun Earth Connection Coronal and Heliospheric Investigation SECCHI Status

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33. SECCHI Summary Schedule

34. Sun Earth Connection Coronal and Heliospheric Investigation SECCHI Program Status (1) Schedule –Reflects additional 12 month launch slip (November 2005) Peer Reviews –Peer reviews held for SCIP, COR1, COR2, EUVI, mechanisms, software and electronics –Peer reviews completed July 9,10 2001 for HI, camera electronics, and focal plane assembly –System peer review 30 July 2001 –Peer reviews will continue during Phase C

35. Sun Earth Connection Coronal and Heliospheric Investigation SECCHI Program Status (2) Preliminary Design Review –Will be held 26, 27 September 2001 at NRL Building 226 auditorium –All are welcome, but if you are interested in attending, send us a note so we can make arrangements.

36. Sun Earth Connection Coronal and Heliospheric Investigation SECCHI Technical Status Design is well along Change in SCIP structure SEB was split into two boxes –Computer system (built by NRL/Space Tech Ctr) –Mechanism controller (built by LMSAL) Fine Pointing System being added to replace the ISS Long lead procurements of CCDs and flight computers under way Descope of high speed link to S/C and hardcopy distribution of all STEREO data to all Co-Is

37. Sun Earth Connection Coronal and Heliospheric Investigation SECCHI SCIP Structure APL is proposing to move SCIP to center of spacecraft – decision in next few days. We will take advantage of the increased volume to implement a simpler structure for the SCIP –Truss box to a honeycomb optical bench –Interfaces to spacecraft must be agreed to very shortly –May help the integration of the harness in the new S/C configuration –Thermal distortion goes in same direction for all telescope tubes –Access may be slightly improved

38. Sun Earth Connection Coronal and Heliospheric Investigation New SCIP Concept GT EUVI COR2 COR1 CEB

39. Sun Earth Connection Coronal and Heliospheric Investigation New SCIP Concept MEB

40. Sun Earth Connection Coronal and Heliospheric Investigation SECCHI Electronics Boxes SEB (SECCHI Electronics Box) –“ Off the shelf” CPU board from NASA/JPL X2000 program Received EM CPU Rad750 board from BAE –MIDEX SWIFT program has designs for similar interfaces to spacecraft and cameras Negotiating to acquire designs for 1355 and 1553 interfaces from GSFC Flight Electronics Branch –New card for housekeeping MEB (Mechanism Electronics Box) –Controllers for all mechanisms except doors –Shares design with Solar-B experiment –Card size same as Solar-B

41. Sun Earth Connection Coronal and Heliospheric Investigation SECCHI IPS Descope EUVI instrument pointing system (IPS) was descoped under the assumption that the S/C pointing would be 1.9 arc sec peak-to-peak But APL doesn’t appear to be willing to guarantee that – so requirement is remaining at 3.8 arc sec which would result in an unacceptable science loss LMSAL has proposed a simpler, open loop system called the Fine Point System (FPS) –FPS receives pointing error information computed by software as opposed to a feedback signal generated by hardware in IPS.

42. Sun Earth Connection Coronal and Heliospheric Investigation Other SECCHI Status Procurements of flight hardware in progress –CCD detectors (Delivery Winter/Spring 2002) –RAD750 CPU board (Delivery Summer 2002) Tests completed, underway or planned –EUVI Acoustic/vibration –COR1 stray light and objective lens erosion –COR2 lens scattered light –HI stray light –Camera interface –CCD control/noise –Rad750 CPU board –Camera GSE hardware and software

43. Sun Earth Connection Coronal and Heliospheric Investigation Other SECCHI Descopes High speed serial interface to spacecraft was eliminated –SECCHI image data was to be transferred over this link at a maximum rate of 450 kbps –Now being transferred over the standard 1553 interface at a maximum data rate of 180 kbps –Requires more memory within SECCHI Distribution of entire STEREO data set to all Co-Is was descoped –Would like discussion later on concepts that SECCHI should follow.

44. Sun Earth Connection Coronal and Heliospheric Investigation SECCHI Communication Technical information: –http://projects.nrl.navy.mil/secchi/index.html Additional informal site –http://stereo.nrl.navy.mil Mail exploders –stereo-all@ares.nrl.navy.mil –stereo-sci@ares.nrl.navy.mil –stereo3d@ares.nrl.navy.mil

45. Sun Earth Connection Coronal and Heliospheric Investigation Upcoming Meetings SECCHI PDRNRL26, 27 September 2001 Spacecraft PDRAPL December 2001 3D WorkshopParis17-20 March 2002