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

2 LSWT meeting, 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

3 LSWT meeting, Venice, 30/03-01/04/2009 SDL inputs  SDL requirements  15 requirements from all instruments except APXS & SD2

4 LSWT meeting, Venice, 30/03-01/04/2009 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 LSWT meeting, Venice, 30/03-01/04/2009 SDL requirements chart –First version

6 LSWT meeting, Venice, 30/03-01/04/2009 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 LSWT meeting, Venice, 30/03-01/04/2009 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 LSWT meeting, Venice, 30/03-01/04/2009 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 LSWT meeting, Venice, 30/03-01/04/2009 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 LSWT meeting, Venice, 30/03-01/04/2009 Used context 1/2  Scheduling : 11/11/ :30 to 11/11/ :30 (30mn before separation to CIVA-P panoramic data transfer)  References dates : ON battery : 11/11/ :30 Separation : 11/11/ :00 Touch Down : 11/11/ :40  Day / Night cycle : D=N=6h15 Beginning date D0 = 11/11/ :00:00 (1 comet day = 12h30mn equator plan )  Lander / Orbiter visibility : No Visibility during SDL, Visibility after Touch Down  Energy : Primary BatterySecondary battery Initial capacity : 1000 Wh. Initial capacity : 98 Wh. Min Threshold capa : 0 Wh. Stop threshold capa : NO. Authorized max Power : 210 W. Authorized max Power : 151 W. Optimization’s Power : 0 W. Integration’s time : 0 s. Initial temperature : 20°C

11 LSWT meeting, Venice, 30/03-01/04/2009 Used context 2/2  Transfer rate to orb : 14Kbits/s  DC/DC Converters efficiency: 50% (TBC) Instruments: LPC  Transfer rate to MM : Nb EXP prioritypriority HIGH MM write In Kbits/s …  Experiment Priority (transfer) : 1 - ROMAP CIVA / ROLIS 3 - MUPUS 4 -SESAME

12 LSWT meeting, Venice, 30/03-01/04/2009 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 LSWT meeting, Venice, 30/03-01/04/2009 Results by instrument 1) SDL Time Line for ROMAP : Romap SLOW Mode

14 LSWT meeting, Venice, 30/03-01/04/2009 Results for Romap 1) Power consumption :  Instrument input : ~=1,7W  Converter input : ~=3,5W 2) Total power asked 3) Residual energy : Er~=994Wh  E bus = 4,65Wh for 1h20

15 LSWT meeting, Venice, 30/03-01/04/2009 1) SDL Time Line for MUPUS : mapper mode, calib, anchor M &T Results by instrument

16 LSWT meeting, Venice, 30/03-01/04/2009 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  E bus ~= 5Wh for 1h

17 LSWT meeting, Venice, 30/03-01/04/2009 1) SDL Time Line for SESAME :health check CAS, DIM, PP PP, DIM-AM, PP, DIM-BM, PP, CAS-TM Results by instrument

18 LSWT meeting, Venice, 30/03-01/04/2009 Results for SESAME 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  E bus ~= 0,4Wh for 1h

19 LSWT meeting, Venice, 30/03-01/04/2009 1) SDL Time Line for ROLIS :Dump, DIT, DIS Results by instrument

20 LSWT meeting, Venice, 30/03-01/04/2009 Results for ROLIS 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  E bus ~= 8Wh for 40mn

21 LSWT meeting, Venice, 30/03-01/04/2009 1) SDL Time Line for CIVA-P : Dump, 2CIVA-P, 7CIVA-P Results by instrument

22 LSWT meeting, Venice, 30/03-01/04/2009 Results for CIVA-P 1) Power consumption :  Instrument input : ~10,5W (Imaging)  Converter input : ~21,5W (Imaging) 2) Total power asked 3) Residual energy : Er~=987Wh  E bus ~= 12.5Wh for 1h26mn

23 LSWT meeting, Venice, 30/03-01/04/2009 1) SDL Time Line for CDMS, PSS, TCU1, TCU2 : Results by sub-systems

24 LSWT meeting, Venice, 30/03-01/04/2009 Results for CDMS, PSS,TCU1, TCU2 1) Power consumption :  Instrument input : ~= 6W  Converter input : ~= 12W 2) Total power asked 3) Residual energy : Er~=966Wh  E bus ~= 24 Wh for 2 hours

25 LSWT meeting, Venice, 30/03-01/04/2009 CDMS, PSS,TCU1, TCU2 with secondary battery 1) Power consumption :  Instrument input : ~= 6W  Converter input : ~= 12W 2) Total power asked 3) Residual energy : Er~=72Wh  E bus ~= 24 Wh for 2 hours

26 LSWT meeting, Venice, 30/03-01/04/2009 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 LSWT meeting, Venice, 30/03-01/04/2009 CDMS, PSS, TCU1, TCU2 Energy 2/2 Energy Wh T°C Battery - 10 ° 0°0° 20 ° Primary Secondary 966 Wh 71,7 Wh71,2 Wh70,7 Wh 963 Wh957 Wh 2) Additional tests: Hypothesis: Primary battery Initial capacity: 1000Wh Secondary battery Initial capacity: 98Wh Residual energy after SDL discharge in function of temperature

28 LSWT meeting, Venice, 30/03-01/04/2009 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 LSWT meeting, Venice, 30/03-01/04/2009 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)