DMSP F16 Special Sensor Magnetometer, SESS/SSM-Boom, Magnetic Field Measurements taken at 850 km, 1 s Data

https://doi.org/10.48322/bh8f-yy31

2023-07-30 12:34:56.789

Defense Meteorology Satellite Program, DMSP, F16 Vector Magnetometer Measurements, 850 km Altitude

R.J. Redmon, Data Access provided by NGDC in Coordination with AFRL and the University of Colorado, Boulder. Please acknowledge the Data Providers. If you find Problems, please report them.

spase://VSPO/NumericalData/DMSP_5D-3/F16/SESS/SSM-Boom/PT1S

Online

Open

CDF

None

R.J. Redmon, Data Access provided by NGDC in Coordination with AFRL and the University of Colorado, Boulder. Please acknowledge the Data Providers. If you find Problems, please report them. Please acknowledge the data providers and CDAWeb when using these data.

Online

Open

CSV

R.J. Redmon, Data Access provided by NGDC in Coordination with AFRL and the University of Colorado, Boulder. Please acknowledge the Data Providers. If you find Problems, please report them. Please acknowledge the data providers and CDAWeb when using these data.

PT1S

Epoch Time

Epoch

Epoch Time, Default

This parameter exhibits an increasing monotonic progression.

PT1S

ms

1e-3>s

01-Jan-1990 00:00:00.000

31-Dec-2029 23:59:59.999

31-Dec-9999 23:59:59.999

Spacecraft Position, ECI

Time series defined by using: EPOCH

SC_ECI

Spacecraft Position, Earth Centered Inertial, ECI, Cartesian Coordinates

Epoch is True of Date, TOD. These ECI Coordinates are calculated from an SPDF SSC Locator 1 min Ephemeris using an Eight Order Interpolation, Burden, R.L., and Faires, J.D., Numerical Analysis, 5th Ed., PWS Publishing Company, Boston, 1993. Using SPDF Methods, the expected Accuracy is on the Order of a few km.

PT1S

km

1e3>m

-7500.0

7500.0

NaN

Spacecraft Latitude, GEO

Time series defined by using: EPOCH

SC_GEOCENTRIC_LAT

Spacecraft Latitude, Geographic Inertial, GEO, Coordinates

Calculated by using IDL Astro Library Function ECI2GEO

PT1S

°

0.0174532925>rad

-90.0

90.0

NaN

Spacecraft Longitude, GEO

Time series defined by using: EPOCH

SC_GEOCENTRIC_LON

Spacecraft Longitude, Geographic Inertial, GEO, Coordinates

Calculated by using IDL Astro Library Function ECI2GEO

PT1S

°

0.0174532925>rad

0.0

360.0

NaN

Spacecraft Geocentric Distance

Time series defined by using: EPOCH

SC_GEOCENTRIC_R

Spacecraft Geocentric Distance

PT1S

km

1e3>m

6378.0

7500.0

NaN

Spacecraft Latitude, AACGM

Time series defined by using: EPOCH

SC_AACGM_LAT

Spacecraft Latitude, Altitude Adjusted Corrected Geomagnetic, AACGM, Coordinates

Calculated by using the SuperDARN AACGM IDL Library. Values are the Result of linearly interpolating between two nearest AACGM 5 Year Epochs.

PT1S

°

0.0174532925>rad

-90.0

90.0

NaN

Spacecraft Longitude, AACGM

Time series defined by using: EPOCH

SC_AACGM_LON

Spacecraft Longitude, Altitude Adjusted Corrected Geomagnetic, AACGM, Coordinates

Calculated by using the SuperDARN AACGM IDL Library. Values are the Result of linearly interpolating between two nearest AACGM 5 Year Epochs.

PT1S

°

0.0174532925>rad

0.0

360.0

NaN

Spacecraft Local Time, AACGM

Time series defined by using: EPOCH

SC_AACGM_LTIME

Spacecraft Local Time, Altitude Adjusted Corrected Geomagnetic, AACGM, Coordinates

Calculated by using the SuperDARN AACGM IDL Library. Values are the Result of linearly interpolating between two nearest AACGM 5 Year Epochs.

PT1S

h

3600>s

0.0

24.0

NaN

Magnetic Field, Spacecraft Frame

Time series defined by using: EPOCH

B_SC_OBS_ORIG

Magnetic Field as originally measured in Spacecraft Frame

X is Geodedic Nadir, Down, Y is along Spacecraft Track, the Ram Direction, Z is Across-Track to the Right. Note, the Pertrubations in this Variable have been recomputed from the Observed B-Field. IGRF11 was run using this Day as Epoch to compute a new, more accurate Geocentric Location that was rotated into Spacecraft Coordinates and then removed.

PT1S

nT

1e-9>T

-100000.0

100000.0

NaN

Delta-B, measured minus IGRF, Spacecraft Frame

Time series defined by using: EPOCH

DELTA_B_SC_ORIG

Delta Magnetic Field, Delta-B, which is equal to the originally measured Magnetic Field minus the International Geomagnetic Reference Field, IGRF, Model Magnetic Field, Spacecraft Frame

X is Geodedic Nadir, Down, Y is along Spacecraft Track, the Ram Direction, Z is Across-Track to the Right

PT1S

nT

1e-9>T

-2000.0

2000.0

NaN

Baseline corrected Delta-B, GEO

Time series defined by using: EPOCH

DELTA_B_GEO

Baseline corrected Delta-B, Geographic, GEO, Spherical, East, North, Up, Coordinates

Finite Differences between adjacent Points on Spacecraft Track were used to determine along Track and across Track Unit Vectors in GEO. No Altitude Change between adjacent Points was assumed. Baseline Correction, F. Rich's MFIT Procedure, is Polynomial Fit every Half-Pass to each Component of Delta-B in Spacecraft Coordinates by using only Data from Regions equatorward of the DMSP Auroral Boundary from the CEDAR Database.

PT1S

nT

1e-9>T

-2000.0

2000.0

NaN

Baseline corrected Delta-B, APX

Time series defined by using: EPOCH

DELTA_B_APX

Baseline corrected Delta-B, Modified Apex, APX, Coordinates, Reference Height 110 km

Coordinates transformed with APEX-PYTHON, NCAR HAO, with Reference Altitude equal to 110 km, See Richmond, J. Geomag. Geoelec., 1995. Baseline Correction, F. Rich's MFIT Procedure, is Polynomial Fit every Half-Pass to each Component of Delta-B in Spacecraft Coordinates by using only Data from Regions equatorward of the DMSP Auroral Boundary from the CEDAR Database.

PT1S

nT

1e-9>T

-2000.0

2000.0

NaN

Baseline corrected Delta-B, Spacecraft Frame

Time series defined by using: EPOCH

DELTA_B_SC

Baseline corrected Delta-B, Spacecraft Frame

X is Geodedic Nadir, Down, Y is along Spacecraft Track, the Ram Direction, Z is Across-Track to the Right. Baseline Correction, F. Rich's MFIT Procedure, is Polynomial Fit every Half-Pass to each Component of Delta-B in Spacecraft Coordinates by using only Data from Regions equatorward of the DMSP Auroral Boundary from the CEDAR Database.

PT1S

nT

1e-9>T

-2000.0

2000.0

NaN

Spacecraft Latitude, APX

Time series defined by using: EPOCH

SC_APEX_LAT

Spacecraft Latitude, Modified Apex Geomagnetic, APXGM, Coordinates, Reference Height 110 km

Calculated by using Apex-Python, which is based on Apex Fortran Code available from CEDAR Database with the nearest Year Epoch

PT1S

°

0.0174532925>rad

-90.0

90.0

NaN

Spacecraft Longitude, APX

Time series defined by using: EPOCH

SC_APEX_LON

Spacecraft Longitude, Modified Apex Geomagnetic, APXGM, Coordinates, Reference Height 110 km

Calculated by using Apex-Python, which is based on Apex Fortran Code available from CEDAR Database with the nearest Year Epoch

PT1S

°

0.0174532925>rad

-180.0

180.0

NaN

Spacecraft Local Time, APX

Time series defined by using: EPOCH

SC_APEX_MLT

Spacecraft Local Time, Modified Apex Geomagnetic, APXGM, Coordinates, Reference Height 110 km

Calculated by using Apex-Python, which is based on Apex Fortran Code available from CEDAR Database with the nearest Year Epoch

PT1S

h

3600>s

0.0

24.0

NaN

Spacecraft Region Code

Time series defined by using: EPOCH

AURORAL_REGION

Spacecraft Region Code: 1=Equatorial, 2=Auroral, 3=Polar

0-No Boundary Identified, 1-Equatorward of the Auroral Zone, 2-Auroral Zone, 3-Polar Cap

PT1S

(2=Auroral)

0.0

3.0

NaN

Auroral Boundary Determination, FOM

Time series defined by using: EPOCH

AURORAL_BOUNDARY_FOM

Auroral Boundary Determination Figure of Merit, FOM: OK if Equal to 2 or Greater

Typical Range 0-4. Less than 2 is Suspect. See the DMSP CDF User Manual for full Specification of FOM Computation.

PT1S

(OK>=2)

0.0

5.0

NaN

Orbit Index by Day

Time series defined by using: EPOCH

ORBIT_INDEX

Integer representing the Orbit of the Day, signed by Hemisphere: >0=Northern, <0=Southern

Orbit Start and End are determined by Crossings of the Apex Magnetic Equator. A value of 0 denotes the first Equator Crossing of the Day.

PT1S

-18.0

18.0

NaN

Spacecraft Ram Velocity Direction, Unit Vector, GEO

Time series defined by using: EPOCH

SC_ALONG_GEO

Spacecraft Ram Velocity Direction, Unit Vector, Geographic, GEO, Coordinates

This is an Estimate, based on a Spherical Trigonometry Approach by using a Great-Circle Arc between adjacent Points, See the User Manual.

PT1S

-1.0

1.0

NaN

Unit Vector across the Spacecraft Track, GEO

Time series defined by using: EPOCH

SC_ACROSS_GEO

Unit Vector across the Spacecraft Track to the Left and Orthogonal to the Spacecraft Ram Velocity Direction, Geographic, GEO, Coordinates

This is an Estimate, based on a Spherical Trigonometry Approach by using a Great-Circle Arc between adjacent Points, See the User Manual.

PT1S

-1.0

1.0

NaN