ResourceName
GOES 2 Magnetic Field Monitor at 3 s Time Resolution in Spacecraft Coordinates
AlternateName
GOES 2 MFM data
ReleaseDate
2023-11-15 12:34:56Z
RevisionHistory
RevisionEvent
ReleaseDate
2023-11-15 10:46:37
Note
Removed bad InformationURLs. Updated AccessURL. Update Format of the data. Updated Parameters.
Description
A biaxial, closed loop, fluxgate magnetometer was deployed on a boom about 0.61 m long. The magnetometer, which had one sensor aligned parallel to the spacecraft spin axis and the other perpendicular to this axis, measured the magnetic field at synchronous altitude. Each sensor had a selectable range (+50, 100, 200, or 400 nT), an offset field capability (plus or minus 1200 nT in 40 nT steps), and an inflight calibration capability.
Acknowledgement
NASA, NOAA, Harold Leinbach, Herbert H. Sauer, Joann Joselyn, Joseph N. Barfield, Howard J. Singer
Contacts
InformationURL
Name
GOES 2 Magnetic Field Monitor
URL
Description
Introduction to the GOES 2 MFM instrument.
PriorIDs
spase://VMO/NumericalData/GOES/2/MFM/PT3S
spase://VSPO/NumericalData/GOES/2/MFM/PT3S
RepositoryID
Availability
Online
AccessRights
Open
AccessURL
Name
Direct access to GOES 2 Biaxial Fluxgate Magnetometer Field Monitor (MFM) Magnetic Field Data
URL
Description
Direct link to the GOES 2 MFM data in CSV (text ascii) format as well as the magnetometer data from other GOES spacecraft. The data are sorted by year. The file names indicates the data type, spacecraft number, year, month, and resolution. For example, M0137607.FIT indicates magnetometer data (M) for spacecraft 1 (01) at 3 s time resolution (3) from July 1976 (7607). Note that spacecraft IDs 91 and 92 refer to SMS satellites, not GOES.
Format
CSV
Encoding
None
Acknowledgement
NASA, Joseph N. Barfield
Name
GOES 1 MFM Magnetic Field Vector 3 s Time Resolution Data in Spacecraft Coordinates
ParameterKey
Magnetic Field Vectors
Description
Magnetic field vector for GOES 1 in spacecraft coordinates in units of 0.1 nT. The values must be divided by a factor of 10 to nT. HP is parallel to the satellite spin axis, which is itself: perpendicular to the orbital plane of the spacecraft. HE lies parallel: to the satellite-earth center line and points earthward. HN is: perpendicular to both HP and HE, and points westward for GOES 1.
Cadence
PT3S
Units
nT
UnitsConversion
0.1>nT
CoordinateSystem
CoordinateRepresentation
Cartesian
CoordinateSystemName
SC
Structure
Size
3
Description
HP is parallel to the satellite spin axis, which is itself: perpendicular to the orbital plane of the spacecraft. HE lies parallel: to the satellite-earth center line and points earthward. HN is: perpendicular to both HP and HE, and points westward for GOES 1.
Element
Name
Hp flux (Northward)
Qualifier
Component.I
Index
1
ParameterKey
hp
Units
nT
UnitsConversion
0.1>nT
ValidMin
-200
ValidMax
+200
FillValue
-99999
Element
Name
He flux (Earthward)
Qualifier
Component.J
Index
2
ParameterKey
he
Units
nT
UnitsConversion
0.1>nT
ValidMin
-200
ValidMax
+200
FillValue
-99999
Element
Name
Hn flux (East)
Qualifier
Component.K
Index
3
ParameterKey
hn
Units
nT
UnitsConversion
0.1>nT
ValidMin
-200
ValidMax
+200
FillValue
-99999
Field
Qualifier
Vector
FieldQuantity
Magnetic
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