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

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SDL inputs SDL requirements

15 requirements from all instruments except APXS & SD2

Instrument Requirement Description Priority CIVA R-SDL-LCI-1 Orbiter imaging 1mn after separation 2 CIVA R-FSS-LCI-1 First panorama imaging 1

CONSERT R-SDL-LCN-1 descent monitoring 1 COSAC ROS-PHI-COS-SDL-001 MS sniffing 3

MUPUS ROS-PHI-MUP-SDL-001 ANC-M and ANC-T measurements during PHILAE touchdown 1

MUPUS ROS-PHI-MUP-SDL-0002 Temperature (infrared) measurements (looking at deep

space). 1

PTOLEMY ROS-PHI-PTO-SDL-001 Sniff mode 3 ROMAP ROS-PHI-ROM-SDL-001 Slow Mode 1Hz continuously 1

ROLIS R-SDL-RLS-1 ROLIS DIT imaging (Descent imaging with Immediate

Transmission) 1

ROLIS R-SDL-RLS-2 ROLIS DIS imaging (Descent Imaging with local Storage) 0.2

Hz starting at Tlanding-15m 1

ROLIS R-SDL-RLS-3 ROLIS DIS image data transfer 1 SESAME ROS-PHI-SES-SDL-001 SESAME-CASSE register the landing impact 1 SESAME ROS-PHI-SES-SDL-002 SESAME-DIM particle flow rate and direction 1

SESAME ROS-PHI-SES-SDL-003 SESAME-DIM Analyze the impact amplitude vs. impact

duration 1

SESAME ROS-PHI-SES-SDL-004 SESAME-PP Monitor electron density variation and the

comet's outgassing activity 2

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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

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SDL requirements chart –First version

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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

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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

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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

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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

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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

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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 HIGHMM write In Kbits/s

1 1 132 1 112 2 103 1 103 2 93 3 84 1 94 2 84 3 74 4 6…

Experiment Priority (transfer) : 1 - ROMAP------------------------------------------ 2 - CIVA / ROLIS

3 - MUPUS 4 -SESAME

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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

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Results by instrument

1) SDL Time Line for ROMAP : Romap SLOW Mode

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Results for Romap1) Power consumption :

Instrument input : ~=1,7W Converter input : ~=3,5W

2) Total power asked

3) Residual energy : Er~=994Wh Ebus = 4,65Wh for 1h20

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1) SDL Time Line for MUPUS : mapper mode, calib, anchor M &T

Results by instrument

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

Results for MUPUS1) 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

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1) SDL Time Line for SESAME : health check CAS, DIM, PP

PP, DIM-AM, PP, DIM-BM, PP, CAS-TM

Results by instrument

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Results for SESAME1) 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

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1) SDL Time Line for ROLIS : Dump, DIT, DIS

Results by instrument

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Results for ROLIS1) 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

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1) SDL Time Line for CIVA-P : Dump, 2CIVA-P, 7CIVA-P

Results by instrument

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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 Ebus ~= 12.5Wh for 1h26mn

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1) SDL Time Line for CDMS, PSS, TCU1, TCU2 :

Results by sub-systems

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Results for CDMS, PSS,TCU1, TCU21) Power consumption :

Instrument input : ~= 6W

Converter input : ~= 12W

2) Total power asked

3) Residual energy : Er~=966Wh Ebus ~= 24 Wh for 2 hours

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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 Ebus ~= 24 Wh for 2 hours

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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

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CDMS, PSS, TCU1, TCU2 Energy 2/2

Energy WhT°C

Battery-10° 0° 20°

Primary

Secondary

966 Wh

71,7 Wh71,2 Wh70,7 Wh

963 Wh957 Wh

2) Additional tests:Hypothesis: Primary battery Initial capacity: 1000WhSecondary battery Initial capacity: 98Wh

Residual energy after SDL discharge in function of temperature

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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

Instruments Data volume

Kbyte Transfer duration: Instr Mem to MM

Transfer duration: MM to Orbiter

CIVA-P orb 250 4 mn 2 mn 20 s MUPUS 16 20 s 9 s ROMAP 41 40 s 23 s ROLIS 1255 21 mn 12 mn

SESAME 506 11 mn 5 mn

CIVA-P pano 875 15 mn 8 mn 20s

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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)