Data Description

This page summarizes information about the selected resource and its origin based on SPASE metadata.

Table of Contents

  1. Product
  2. Repository
  3. Instruments
  4. Observatory
  5. Persons

SPASE version 2.0.1

Numerical Data Product: GOES 10 Magnetometer 1-Minute Data

Resource ID
spase://VMO/NumericalData/GOES10/MAG/PT1M Get XML
Name
GOES 10 Magnetometer 1-Minute Data
Description

The NOAA Geostationary Operational Environment Satellite (GOES) key parameters. This data is a subset of the data available from the GOES Space Environment Monitor (SEM) instruments. It contains vector magnetic field in three coordinate systems: (1) Spacecraft P,E,N (2) GSM x,y,z and (3) GSE x,y,z. Spacecraft magnetic field is defined as: P - perpendicular to the spacecraft orbital plane or parallel to the Earth's spin axis in the case of a zero degree inclination orbit; E - perpendicular to P and directed earhtwards; and N - perpendicular to both P and E and directed eastwards.

Additional information
Geostationary Satellite Server

A web site hosted by NOAA with information and links to the GOES spacecraft and data

Acknowledgement

Users should acknowledge the CDAWeb for providing access to the data as well as the PI H. Singer and originating institution NOAA Space Environment Center

Contact
Role Person
1. Principal investigator Dr. Howard J. Singer Get XML
Release date
2009-07-15 22:15:10
Repository
Name
CDAWeb Data Repository FTP Interface Get XML
Availability
Online
Access rights
Open
URL
1-minute GOES 10 MAG data at CDAWeb

An ftp repository hosting 1-minute GOES 10 MAG data

Format
CDF
Encoding
None
Provider processing level
Level 2
Provider resource name
GOES_10
Provider version
3
Instruments
GOES 10, Triaxial Fluxgate Magnetometer Get XML
GOES 10 Position Get XML
Measurement type
Ephemeris
Magnetic field
Temporal description
Start date
1999-03-21 00:00:00
Stop date
2006-06-22 23:59:59
Cadence
1 minute
Observed regions
Earth.Magnetosphere
Keywords
Magnetic field
↑

Parameters

Parameter #1

Name
Epoch
Parameter key
Epoch
Description

Epoch of the data point

Cadence
1 minute
Units
Milliseconds
Valid minimum
01-Jan-1977 00:00:00.000
Valid maximum
31-Dec-2010 00:00:00.000
Fill value
-1.0e+31
Parameter type
Temporal

Parameter #2

Name
Time PB5
Parameter key
Time_PB5
Description

Time array in the form [year, day of year, millisecond]

Cadence
1 minute
Valid minimum
01-Jan-1977 00:00:00.000
Valid maximum
31-Dec-2010 00:00:00.000
Fill value
-2147483648
Parameter type
Temporal

Parameter #3

Name
Magnetic Field Vector GSE
Parameter key
B_GSE_c
Description

Magnetic Field vector in GSE coordinates

Cadence
1 minute
Units
nT
Coordinate system
Cartesian GSE
Structure
Elements
Index Name
1 Xgse
2 Ygse
3 Zgse
Valid minimum
-600.00
Valid maximum
600.00
Fill value
-1.0e+31
Quantity
Magnetic field
Qualifier
Vector

Parameter #4

Name
Magnetic Field vector GSM
Parameter key
B_GSM_c
Description

Magnetic Field vector in GSM coordinates

Cadence
1 minute
Units
nT
Coordinate system
Cartesian GSM
Structure
Elements
Index Name
1 Xgsm
2 Ygsm
3 Zgsm
Valid minimum
-600.0
Valid maximum
600.0
Fill value
-1.0e+31
Quantity
Magnetic field
Qualifier
Vector

Parameter #5

Name
Magnetic Field vector spacecraft coordinates
Parameter key
B_lcl_c
Description

Magnetic Field vector in spacecraft coordinates. Spacecraft magnetic field (P,E,N) is defined as: P - perpendicular to the spacecraft orbital plane or parallel to the Earth's spin axis in the case of a zero degree inclination orbit; E - perpendicular to P and directed earhtwards; and N - perpendicular to both P and E and directed eastwards.

Cadence
1 minute
Units
nT
Coordinate system
Cartesian SpacecraftOrbitPlane
Structure
Elements
Index Name
1 P
2 E
3 N
Valid minimum
-600.0
Valid maximum
600.0
Fill value
-1.0e+31
Quantity
Magnetic field
Qualifier
Vector

Parameter #6

Name
Spacecraft Position Geographic
Parameter key
SC_pos_ll
Description

Spacecraft position in Geographic coordinates

Cadence
1 minute
Units
[degrees,degrees,km]
Coordinate system
Spherical GEO
Structure
Elements
Index Name Units Valid min Valid max
1 Latitude degrees -90 90
2 Longitude degrees 0 360
3 Radius km 50 50000
Fill value
-1.0e+31
Parameter type
Positional

Parameter #7

Name
Spacecraft position GEO
Parameter key
SC_pos_eo
Description

Spacecraft position in GEO coordinates

Cadence
1 minute
Units
km
Coordinate system
Cartesian GEO
Structure
Elements
Index Name
1 X GEO
2 Y GEO
3 Z GEO
Valid minimum
-5000.0
Valid maximum
5000.0
Fill value
-1.0e+31
Parameter type
Positional

Parameter #8

Name
Spacecraft Position GSE
Parameter key
SC_pos_se
Description

Spacecraft position in GSE coordinates

Cadence
1 minute
Units
km
Coordinate system
Cartesian GSE
Structure
Elements
Index Name
1 GSE X
2 GSE Y
3 GSE Z
Valid minimum
-5000.0
Valid maximum
5000.0
Fill value
-1.0e+31
Parameter type
Positional

Parameter #9

Name
Spacecraft position GSM
Parameter key
SC_pos_sm
Description

Spacecraft position in GSM coordinates

Cadence
1 minute
Units
km
Coordinate system
Cartesian GSM
Structure
Elements
Index Name
1 X GSM
2 Y GSM
3 Z GSM
Valid minimum
-5000.0
Valid maximum
5000.0
Fill value
-1.0e+31
Parameter type
Positional

Parameter #10

Name
MGF Instrument Status
Parameter key
MGF_stat
Description

Status of the magnetic field instrument; 0 = ok, 1 = minor problem, 2 = major problem, 3 = missing data

Cadence
1 minute
Parameter type
Other

Parameter #11

Name
Mag post-gap flag
Parameter key
B_flag
Description

Magnetic field data flag; 0 = no gap, 1 = data not available

Cadence
1 minute
Parameter type
Other

Parameter #12

Name
Spacecraft post-gap flag
Parameter key
SC_flag
Description

Spacecraft location data flag; 0 = no gap, 1 = data not available

Cadence
1 minute
Parameter type
Other
↑

SPASE version 2.0.0

Instrument: GOES 10, Triaxial Fluxgate Magnetometer

Instrument ID
spase://SMWG/Instrument/GOES10/MAG Get XML
Name
GOES 10, Triaxial Fluxgate Magnetometer
Description

The magnitude and direction of the magnetic field are measured by two redundant Schonstedt triaxial magnetometers located on a boom 3 m, and 2.7 m away from the spacecraft body. The electronics are located inside the body. The X, Y, Z component signals from the three axes are digitized by a 16-bit converter, at a sampling rate of 0.512 s. The sensitivity is 0.1 nT, and the range +/- 1000 nT. After temperature correction, and before (undescribed) stray-field correction, the accuracy is at about 1 nT level.

Contact
Role Person
1. Principal investigator Dr. Howard J. Singer Get XML
Release date
2009-05-20 21:10:12
Instrument type
Magnetometer
Investigation name
GOES 10, Triaxial Fluxgate Magnetometer on GOES 10
Observatory
GOES 10 Get XML
↑

SPASE version 2.0.0

Instrument: GOES 10 Position

Instrument ID
spase://SMWG/Instrument/GOES10/Ephemeris Get XML
Name
GOES 10 Position
Alternate name
GOES 10 Ephemeris
Description

GOES 10 spacecraft position

Contact
Role Person
1. Principal investigator Dr. Howard J. Singer Get XML
Release date
2009-05-20 21:10:12
Instrument type
Platform
Investigation name
Spacecraft position
Observatory
GOES 10 Get XML
↑

SPASE version 2.0.0

Observatory: GOES 10

Observatory ID
spase://SMWG/Observatory/GOES10 Get XML
Name
GOES 10
Alternate name
1997-019A
Description

The Geostationary Operational Environmental Satellite GOES 10 is the third satellite in a series of next generation geosynchronous spacecraft, referred to as GOES-NEXT and represented by the GOES I through GOES M spacecraft. The GOES-NEXT series is a joint effort on the part of NASA and NOAA to provide continued operational monitoring of weather systems primarily over the United States, distribute meteorological data to regional and national weather offices within the USA, contribute to the development of an environmental data collection network, contribute to the search and rescue program, improve the capability for forcasting and provide real-time warnings of solar distrubances, and to extend knowledge and understanding of atmospheric processes to improve short and long-term weather forecasts.

The GOES-NEXT series extends the capabilities of the previous GOES 1-7 spacecraft. The GOES I-M spacecraft will be placed over the equator at 135 deg West or 75 deg West. The design allows unobstructed views of the Earth for operational coverage by the spacecraft sensors. The spacecraft configuration is a compact box-shaped main body that carries the Earth-observing instruments, a continuous-drive solar array attached to the south panel through a yoke assembly, and a solar pointing instrument gimbal mounted on the solar panel yoke. The main body accomodates the sensors, electronics, and support subsystems. The communication antennas, except the Tracking, Telemetry, and Command (TT&C) antenna, are hard-mounted to the Earth-facing panel. The Propulsion Module consists of the fuel and oxidizer tanks for the bipropellant propulsion subsystem mounted on the central cylinder. The Attitude and Orbit Control Substem (AOCS) provides attitude control of the spacecraft. The AOCS consists of the sensors, electronics, and the actuators. The GOES power is generated from the solar array and two 12 A-hr batteries. Power is automatically regulated during solar eclipses. A conical shaped solar sail at the end of a 58-foot boom balances torque caused by solar radiation. The main body of the spacecraft is a 2-meter cube. In its deployed orbit configuration, the overall length is about 27 meters. Initial mass was about 4640 pounds, including fuel. Design lifetime is about five years.

The Image Navigation/Registration (INR) system provides Imager and Sounder data products in real-time to users. The Communications, Command, and Data Handling subsystem is comprised of antennas, receivers, transponders, transmitters, data encoders and encryptors and multiplexers. The Tracking Telemetry and Command (TT&C) subsystem provides the necessary monitor and command link between the spacecraft and the ground stations.

The GOES-NEXT instruments consist of the following: (1) Earth Imaging System, a 5-channel visible and infrared radiometer which provides Earth imagery 24 hours a day; (2) Sounding System, a 19-channel discrete-filter radiometer for obtaining atmospheric temperature and moisture soundings; (3) a Space Environment Monitor (SEM), which consists of a magnetic field sensor, a solar X-ray sensor, an energetic particle sensor (EPS), and a High Energy Proton and Alpha Detector (HEPAD); (4) a Search and Rescue subsystem (SARSAT), which receives signals from 406 MHz distress beacons and relays them to the ground; (5) a Data Collection System (DCS) for collecting and relaying real-time information from Data Collection Platforms (DCPs) such as buoys, balloons, remote weather stations, ships, and aircraft; and (6) a Weather Facsimile (WEFAX) system which relays processed weather imagary from the Wallops Island station to the user community. The SEC package has been frequently eratic during 2003.

Additional information
NSSDC's Master Catalog

Information about the GOES 10 mission

Contact
Role Person
1. General contact UNKNOWN Get XML
Release date
2009-05-20 20:00:12
Observatory group
GOES
Location
Region
Heliosphere.NearEarth
↑

SPASE version 2.0.0

Person: Dr. Howard J. Singer

Name
Dr. Howard J. Singer
Organization
NOAA Environmental Research Labs
Person ID
spase://SMWG/Person/Howard.J.Singer Get XML
↑

SPASE version 2.0.0

Person: Dr. Robert E. McGuire

Name
Dr. Robert E. McGuire
Organization
NASA Goddard Space Flight Center
Address
Code 672, Greenbelt, MD 20771, USA
Email
mcguire@mail630.gsfc.nasa.gov
Phone
1-301-286-7794
Person ID
spase://SMWG/Person/Robert.E.McGuire Get XML
Release date
2007-05-30 15:25:24
↑

SPASE version 2.0.0

Person: UNKNOWN

Name
UNKNOWN
Organization
UNKNOWN
Person ID
spase://SMWG/Person/UNKNOWN Get XML
Release date
1999-01-01 00:00:00
↑

SPASE version 1.2.0

Repository: CDAWeb Data Repository FTP Interface

Repository ID
spase://SMWG/Repository/NASA/GSFC/SPDF/CDAWeb Get XML
Name
CDAWeb Data Repository FTP Interface
Description

Coordinated Data Analysis Web (CDAWeb) supports not only interactive plotting of variables from multiple instruments on multiple investigations simultaneously on arbitrary, user-defined time-scales. It also supports data retrieval in various formats using its interactive web interface or ftp service.

Additional information
CDAWeb Home Page

Coordinated Data Analysis Web (CDAWeb) home page at Space Physics Data Facility of the NASA Goddard Space Flight Center.

Contact
Role Person
1. Project scientist Dr. Robert E. McGuire Get XML
Release date
2008-08-26 21:14:34
Prior ID
spase://VMO/Repository/CDAWeb
↑