Information about the Auto-compatibility of inter-instrument interference campaign during the NECP.
Working Group Members
- Eric Lorfevre (RPW system, WG leader)
- Milan Maksimovic (RPW PI)
- Xavier Bonnin (ROC manager)
- Antonio Vecchio (RPW operations scientist)
- Diane Berard (RPW operations engineer)
- Jean-Michel Travert (RPW command/control)
RPW sub-system teams will also contribute to define the RPW modes to be set during the deployement.
Contact at MOC
- Sylvain dot Lodiot at esa dot int
Description of the operation
Context and objectives
The main purpose of this campaign, occurring during the NECP phase, is to characterize the Solar Orbiter payload EMC in space by acquiring RPW data.
RPW will run measurements covering the full frequency range for both magnetic and in electric sensors, in normal and burst mode. At the beginning of the campaign all the Solar Orbiter Instruments are OFF. Then they are successively set to ON. RPW will thus analyze the influence of each instrument on its measurements and on the background noise.
The EMC ground campaign planned on 2019 might be a good baseline to prepare this operation (TBC).
Operation timeline and instrument configuration overview
Fig. 1. Inter instrument interference campains operation timeline
| Activity | Step | Description | Time since beginning |
|---|---|---|---|
| Instrument initialization | A | RPW switch on and go to SBM detection mode | 0 min |
For each step, several configurations need to be tested :
| A-B | Run steps 1 to 13 (see next table) RPW measurements will covering the full frequency range for both electric and magnetic sensors | 80 min x13 |
| Payload switch off (except RPW) | C | Switch off all instruments except RPW | 1040 min min |
| RPW switch off | D | RPW switch off | 1040+TBD min |
The switch on sequence is shown in table below:
STEP Num. |
|
RPW |
MAG |
EPD |
SWA |
PHI |
EUI |
SPICE |
STIX |
METIS |
SOLOHI |
A1 |
T0 to T1=T0 + 80 min
|
ON |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
A2 |
T1 to T2=T1 + 80 min
|
ON |
ON |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
A3 |
T2 to T3=T2 + 80 min
|
ON |
OFF |
ON |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
A4 |
T3 to T4=T3 + 80 min
|
ON |
OFF |
OFF |
ON |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
A5 |
T4 to T5=T4 + 80 min
|
ON |
OFF |
OFF |
OFF |
ON |
OFF |
OFF |
OFF |
OFF |
OFF |
A6 |
T5 to T6=T5 + 80 min
|
ON |
OFF |
OFF |
OFF |
OFF |
ON |
OFF |
OFF |
OFF |
OFF |
A7 |
T6 to T7=T6 + 80 min
|
ON |
OFF |
OFF |
OFF |
OFF |
OFF |
ON |
OFF |
OFF |
OFF |
A8 |
T7 to T8=T7 + 80 min
|
ON |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
ON |
OFF |
OFF |
A9 |
T8 to T9=T8 + 80 min
|
ON |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
ON |
OFF |
A10 |
T9 to T10=T9 + 80 min
|
ON |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
ON |
A11 |
T10 to T11=T10 + 80 min
|
ON |
ON |
ON |
ON |
OFF |
OFF |
OFF |
OFF |
OFF |
OFF |
A12 |
T11 to T12=T11 + 80 min
|
ON |
OFF |
OFF |
OFF |
ON |
ON |
ON |
ON |
ON |
ON |
A13 |
T12 to T13=T12 + 80 min
|
ON |
ON |
ON |
ON |
ON |
ON |
ON |
ON |
ON |
ON |
B |
T13 to T14=T13 + TBD min
|
All instruments OFF except RPW Auto compatibility with the platform - Changes in high gain antenna angle - Effects of high gain antenna radiation on preamplifiers - Changes in solar panel angles
| |||||||||
Table.1. Switch on sequence. Red and blue refer to in-situ and remote sensing instruments, respectively.
The table below gives the RPW configurations expected over the operation timeline.
| First step | Last step | RPW configurations | Duration | Comment |
|---|---|---|---|---|
| A1 | A2 |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| A2 | A3 |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| A3 | A4 |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| A4 | A5 |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| A5 | A6 |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| A6 | A7 |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| A7 | A8 |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| A9 | A10 |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| A10 | A11 |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| A10 | A11 |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| A11 | A12 |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| A12 | A13 |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| A13 | B |
| 80 min. | There are 9 configurations executed over the 80 mins. |
| B | C |
| TBD min. | There are 9 configurations executed over the TBD mins. |
Orbitography
TBW
Success criteria
TBW
Operational constraints, assumptions and dependencies
Resources allocation
Power consumption allocation
TBW
Telemetry allocation
TBW
Instrument-related constraints, assumption and dependencies
The DPU SCIENCE SBM_DETECTION submode can be applied on-board during NECP, but there is not guarantee that the resulting SBM data stored on the SSMM can be downlinked to ground by MOC during this phase. (Note that the dump of the SBM data by the DPU can be forced by TC, since in the nominal case the transfer of data from the DPU SBM buffers to the SSMM is only done when an event is detected on-board.)
Spacecraft-related constraints, assumption and dependencies
TBW
Ground constraints, assumption and dependencies
TBW
Related resources
Meeting notes
Action items
Attached Items
- TDS configuration :
- LFR configuration :