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SDL : MOST point of view CNES / J-F Fronton / D Hallouard LSWT Venice , 30/03-01/04/2009

SDL : MOST point of view CNES / J-F Fronton / D Hallouard LSWT Venice , 30/03-01/04/2009. Inputs. Instrument Flight Operation Plan Today status: all except Sesame, Ptolemy, Cosac IFOP Complementary to Science Objectives doc Merge of the documents and extraction of SDL & LTS requirements.

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SDL : MOST point of view CNES / J-F Fronton / D Hallouard LSWT Venice , 30/03-01/04/2009

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  1. SDL: MOST point of viewCNES / J-F Fronton / D Hallouard LSWT Venice, 30/03-01/04/2009

  2. Inputs • Instrument Flight Operation Plan • Today status: all except Sesame, Ptolemy, Cosac • IFOP Complementary to Science Objectives doc • Merge of the documents and extraction of SDL & LTS requirements

  3. SDL inputs • SDL requirements • 15 requirements from all instruments except APXS & SD2

  4. SDL inputs • SDL requirements • SDL working group selected the requirements from:- CIVA (orbiter imaging and panoramic)- MUPUS (Calibration and Anchoring measurement)- ROMAP in Slow mode- ROLIS (DIT and DIS)- SESAME (PP, DIM,CASSE)- a total of 12 requirements

  5. SDL requirements chart –First version

  6. METHODOLOGY 1/4 1) Library: • For each instrument creation of sequences based on requirement or LIOR • Each sequence includes one or several tasks • Sequences can be combined to create macro-sequences

  7. METHODOLOGY 2/4 2) Sequence Plan: • Built by assembling sequences • Macroscopic and sequential view of the activities • Association of this plan to a context file • Generation of the final plan

  8. METHODOLOGY 3/4 3) Scenario: • Customizable plan (add, modify, delete) • Each color is a chain : sub-system or experiment • Sequences are displayed in tasks • All boxes and links are configurable

  9. METHODOLOGY 4/4 • Generic scenario:The scenario presents the activities independently of the application context (time, energy source, temperature, data rate, visibilities, day / night cycle) • Context description:- set of applicable parameters- different contexts are induced by landing site, attitude, platform etc … - different contexts can be applied to the same scenario

  10. Used context 1/2 • Scheduling : 11/11/2014 11:30 to 11/11/2014 13:30 (30mn before separation to CIVA-P panoramic data transfer) ---------------- • References dates : -------------------------- ON battery : 11/11/2014 11:30 Separation : 11/11/2014 12:00 Touch Down : 11/11/2014 12:40 • Day / Night cycle : D=N=6h15 Beginning date D0 = 11/11/2014 11:00:00 (1 comet day = 12h30mn equator plan ) ----------------------- • Lander / Orbiter visibility : No Visibility during SDL, Visibility after Touch Down ----------------------------------- . • Energy : ------------ Primary Battery Secondary battery ---------------------- -------------------------- . Initial capacity : 1000 Wh . Initial capacity : 98 Wh . Min Threshold capa : 0 Wh . Min Threshold capa : 0 Wh . Stop threshold capa : NO . Stop threshold capa : NO . Authorized max Power : 210 W . Authorized max Power : 151 W . Optimization’s Power : 0 W . Optimization’s Power : 0 W . Integration’s time : 0 s . Integration’s time : 0 s . Initial temperature : 20°C . Initial temperature : 20°C

  11. Used context 2/2 • Transfer rate to orb : 14Kbits/s --------------------------- • DC/DC Converters efficiency: 50% (TBC) Instruments: LPC ----------------------------------------- • Transfer rate to MM : ---------------------------- Nb EXP priority priority HIGH MM write In Kbits/s 1 1 13 2 1 11 2 2 10 3 1 10 3 2 9 3 3 8 4 1 9 4 2 8 4 3 7 4 4 6 … • Experiment Priority (transfer) :1 - ROMAP ------------------------------------------ 2 - CIVA / ROLIS 3 - MUPUS 4 -SESAME

  12. MOST Process  MOST performs accurately the energy management  MOST needs improvements regarding the data transfers & management (cf. MOST CDMS simulation). Data management is one of the highest constraint (indirect & calculated) with energy and thermal. • Therefore:- result of global planning is not realistic- presentation of results instrument by instrument - energy profiles and quantities - data volume - data transfer duration calculated in view of GRM tests performance

  13. Results by instrument 1) SDL Time Line for ROMAP : Romap SLOW Mode

  14. 1) Power consumption : • Instrument input : ~=1,7W • Converter input : ~=3,5W 2) Total power asked 3) Residual energy : Er~=994Wh Ebus = 4,65Wh for 1h20 Results for Romap

  15. Results by instrument 1) SDL Time Line for MUPUS : mapper mode, calib, anchor M &T

  16. Results for MUPUS 1) Power consumption :map, calib, anchor • Instrument input : ~2; 5; 2W • Converter input: ~4,5; 10; 4W 2) Total power asked 3) Residual energy :Er~=993Wh Ebus ~= 5Wh for 1h

  17. Results by instrument 1) SDL Time Line for SESAME : health check CAS, DIM, PP PP, DIM-AM, PP, DIM-BM, PP, CAS-TM

  18. 1) Power consumption :(HC,PP,DIM-AM,DIM-BM,CAS-TM) • Instrument input : ~0,7; 0,25; 0,1; 0,7W • Converter input : ~1,3; 0,5; 0,2; 1,3W 2) Total power asked 3) Residual energy :Er~=999,7Wh Ebus ~= 0,4Wh for 1h Resultsfor SESAME

  19. Results by instrument 1) SDL Time Line for ROLIS : Dump, DIT, DIS

  20. 1) Power consumption : • Instrument input : ~6(DIT); 8(DIS)W • Converter input : ~12,5(DIT); 16(DIS) 2) Total power asked 3) Residual energy :Er~=993Wh Ebus ~= 8Wh for 40mn Results for ROLIS

  21. Results by instrument 1) SDL Time Line for CIVA-P : Dump, 2CIVA-P, 7CIVA-P

  22. 1) Power consumption : • Instrument input : ~10,5W (Imaging) • Converter input : ~21,5W (Imaging) 2) Total power asked 3) Residual energy : Er~=987Wh Ebus ~= 12.5Wh for 1h26mn Results for CIVA-P

  23. Results by sub-systems 1) SDL Time Line for CDMS, PSS, TCU1, TCU2 :

  24. 1) Power consumption : • Instrument input : ~= 6W • Converter input :~= 12W 2) Total power asked 3) Residual energy :Er~=966Wh Ebus ~= 24 Wh for 2 hours Results for CDMS, PSS,TCU1, TCU2

  25. 1) Power consumption : • Instrument input : ~= 6W • Converter input :~= 12W 2) Total power asked 3) Residual energy :Er~=72Wh Ebus ~= 24 Wh for 2 hours CDMS, PSS,TCU1, TCU2 with secondary battery

  26. CDMS, PSS, TCU1, TCU2 Energy 1/2 1) Theory: • At battery level the total available energy is function of temperature and current. • Primary battery theoretical initial capacity (discharge 56mA, 20°C)= 1491 Wh • Secondary battery theoretical initial capacity (discharge 60mA , 20°C)= 151 Wh • Primary battery theoretical estimated capacity in 2014(capacity lost 10,2%, for discharge current 56mA and 20°C)= 1339 Wh • Secondary battery theoretical estimated capacity in 2014 ( capacity lost 19% and charge at 95%, discharge current 60mA and 20°C) = 116 Wh

  27. T°C -10° 0° 20° Energy Wh Battery 966 Wh Primary 957 Wh 963 Wh Secondary 70,7 Wh 71,2 Wh 71,7 Wh CDMS, PSS, TCU1, TCU2 Energy 2/2 2) Additional tests:Hypothesis: Primary battery Initial capacity: 1000WhSecondary battery Initial capacity: 98Wh Residual energy after SDL discharge in function of temperature

  28. SDL additional results • SDL data volume and transfer duration Priority data rate IM to MM- ROMAP 1 9 Kb/s- CIVA & ROLIS 2 8 Kb/s- MUPUS 3 7 Kb/s - SESAME 4 6 Kb/s Data rate MM to Orbiter: 14 Kb/s

  29. SDL analysis comments • Data management is one of the highest constraint (indirect & calculated) with energy and thermal. • SDL scheduling is very time constraint • Low degree of freedom to optimize energy profile and data transfer periods • All inputs should be re-evaluated in view of the flight data • First study of a long series of iterations with different scenario and contexts (inputs & feedback from scientists)

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