Minimize GOES-N, O, P Satellites

GOES-N, O, P Satellites (extended 2nd generation series)

Spacecraft   Launch   Operational Status   Sensor Complement    References

For a number of years the designation GOES-Next (N) was used to identify the first of the satellites that would follow the GOES I-M series. It was also thought this GOES-N would be the start of a totally new generation satellite series. However, during the time frame of about 1992-95, NOAA and NASA have come to realize that a new generation satellite series would take at least a decade to define, develop, manufacture, and to launch. This new situation made both parties (NOAA, NASA) realize it would need a few more clones of the current GOES I-M series to maintain continuity of GOES service prior to the GOES Next being available.

What has evolved is a program that is buying 3-4 additional GOES I-M satellites beyond the GOES I-M series. These will then be labeled GOES N through Q. GOES-R is considered to be the first of a new 3rd generation of three-axis stabilized satellites with an entirely new sensor complement - comprised of improved spacecraft and instrument technologies. The definition phase of this 3rd generation program started in 2000 (information provided by Roger Heymann of NOAA).

In January 1998, BSS (Boeing Satellite Systems Inc. of El Segundo, CA (formerly Hughes Space and Communications Company), was awarded a contract from NASA/GSFC to design, manufacture, and launch two GOES satellites, namely GOES-N and -O (with two options for -P and -Q). However, the GOES-Q option spacecraft was cancelled in 2004. The GOES-N,O,P contract is fixed price with delivery on-orbit. Note: the former BSS was in turn renamed to BSIS (Boeing Space and Intelligence Systems). 1) 2)

The major goals of the extended 2nd generation GOES program are:

• To maintain continuous, reliable operational, environmental, and storm warning systems to protect life and property

• To monitor the Earth's surface and space environmental conditions

• To introduce improved atmospheric and oceanic observations and data dissemination capabilities

• To develop and provide new and improved applications and products for a wide range of US agencies, state and local governments, and private users.

GOES-8
(GOES-I)

Apr. 13, 1994

First second generation S/C (3-axis stabilized); S&RSAT became operational on GOES-8; GOES-8 operated for over 6.5 years (design life of 3 years). GOES-8 was functioning at 75º W. The S/C was deactivated on May 5, 2004 and boosted into a higher orbit (350 km above GEO)

2 nd Generation S/C

(built by SSL/Loral)

GOES-9
(GOES-J)

May 23, 1995

GOES-I to -M S/C were built by SS/L; In July 2002, GOES-9 was removed from operational service in 1998 - to act as backup for GMS-5 of Japan, starting in 2003

GOES-10
(GOES-K)

April 25, 1997

In the initial mission, the S/C suffered a solar array malfunction. A recovery procedure was performed to invert the S/C and operate the solar array in the reverse direction. The S/C became operational in July 1998. It replaces GOES-9 which had problems with its attitude control system. GOES-10 is positioned at 135º W. The design life of KLM S/C is 5 years.
GOES-10 was decommissioned on Dec. 2, 2009.

GOES-11
(GOES-L)

May 3, 2000

GOES-11 was launched into a storage orbit at 105º W (backup)

GOES-12
(GOES-M)

July 23, 2001

GOES-M is the last of the 2nd generation S/C built by SS/L
Began operations on April 1, 2003
Repositioned to support South America in May 2010
Decommissioned in August 2013

GOES-13
(GOES-N)

May 24, 2006

GOES-N, and -O (options for -P and -Q) S/C are being built by BSS (Boeing Satellite Systems) on a Boeing 601 S/C platform, the S/C feature a star tracker for pointing

2nd Generation S/C extended, built by BSIS (Boeing Space and Intelligence Systems)

GOES-14
(GOES-O)

June 27, 2009

NASA contracted with BSIS (Boeing Space and Intelligence Systems) to build and launch the GOES-O spacecraft. About 3 weeks after launch, control is turned over to NASA. About 5 months later, NASA will transfer operational control of GOES-14 to NOAA. The S/C will be stored on orbit and available for activation should one of the operational GOES satellites degrade or exhaust its fuel..

GOES-15
(GOES-P)

March 4, 2010

GOES-P was built for NASA and NOAA by BSIS. GOES-15 was placed in on-orbit storage as a replacement for an older GOES satellite

GOES-Q

 

NOAA may not exercise the option for GOES-Q; - In fact, GOES-Q was cancelled in 2004

GOES-R

Nov. 19, 2016

Start of 3rd generation satellites and instruments (ABI, SUVI, EXIS, GLM, SEISS, MAG)

3 rd Generation S/C
built by Lockheed Martin Space Systems Company, Denver

GOES-S

2018 planned

 

Table 1: Overview of GOES 2nd generation extended S/C launches

GOES_NOP_Auto10

Figure 1: Continuity of the GOES program as of January 2016 (image credit: NOAA) 3)

 


 

Spacecraft:

The space segment of GOES is comprised of two spacecraft in orbit, one located nominally at 75º W and one at 135º W. The GOES-N-P series spacecraft are based on the BSS 601 platform (El Segundo, CA), a three-axis body stabilized bus design providing continuous observations of dynamic events in real-time and enhanced pointing capabilities for more accurate localization of severe storms and other weather phenomena, resulting in more precise warnings to the public. 4) 5) 6) 7) 8)

GOES_NOP_AutoF

Figure 2: Illustration of the GOES-N spacecraft configuration (image credit: NASA, NOAA)

Spacecraft bus size

Length = 4.2 m, width = 1.88 m

Spacecraft on-orbit configuration

Length = 8.4 m, (solar array to spacecraft body)
Height = 9.1 m (Imager port to magnetometer boom)
Depth = 2.9 m

Solar array panel

8.2 m, yoke panel = 2.3 m x 1.8 m
Panel of dual-junction gallium arsenide (GaAs) solar cells

Spacecraft launch mass

3,209.5 kg, dry mass = 1,543 kg

Spacecraft power

2.3 kW at BOL, 2 kW at EOL (End of Life)
Battery: 24 NiH2 cells, capacity = 123 Ah

Propulsion (liquid apogee motor)

Fuel: Monomethylhydrazine, 490 N
Oxidizer: Nitrogen Tetroxide
Pressurant: Helium

Stationkeeping thrusters (12)

9 N, each, bipropellant

Spacecraft design life

- Five years of operations plus two years of on-orbit storage
- Five years of ground storage is also possible

RF communications

S-band: 9 downlinks, 5 uplinks (include telemetry and command data)
L-band: 8 downlinks
UHF: 1 downlink, 2 uplinks

Antennas

3 S/L Band, cup-shaped with dipole
2 T&C antennas and 1 Omni antenna (aft)
1 UHF, cup-shaped with dipole

Table 2: Overview of GOES-N spacecraft parameters

The power subsystem has been improved with the use of a single panel solar array that contains high-efficiency dual-junction gallium-arsenide (GaAs) solar cells.

BSIS provides the communication subsystem along with a search and rescue capability (GEOS&R) to detect distress signals from the ground segment. BSS also integrates three government-provided primary observation instruments.

The GOES N-P series delivers considerably improved INR (Image Navigation and Registration) performance compared to that of the previous generation. The GOES-N spacecraft is entirely new and includes advanced GN&C (Guidance, Navigation, and Control) features and improved instrument accommodations that enable dramatically improved INR performance within an evolved version of the GOES I-M INR architecture.

The new INR features include: 9) 10)

• SIAD (Stellar Inertial Attitude Determination) for fine attitude determination determination, consisting of three star trackers and a hemispherical resonating gyroscope package

• Optical bench accommodations for the Imager and Sounder instruments

• IMC (Image Motion Compensation) implementation improvements

• Closed-loop DMC (Dynamic Motion Compensation) that is added to the IMC to compensate for residual attitude control error - replacing the open-loop MMC (Mirror Motion Compensation) and SMC (Spacecraft Motion Compensation) of the GOES I-M series

• ISEC (Instrument Systematic Error Compensation) to compensate for systematic scan errors that are functions of scan coordinates

• INR operations to accommodate thruster maneuvers for momentum

• INR operations for continuous operation across eclipses

• INR operations following yaw flips.

SIAD (Stellar Inertial Attitude Determination) is an advanced attitude sensor of the GOES-N to P series spacecraft AOCS, developed at BSIS. The requirements call for a pointing accuracy of < 0.01º and to use SIAD as a mirror controller for the GOES Imager and GOES Sounder instruments in real-time (dynamic compensation of S/C jitters to an accuracy of 10 µrad, 3σ). This technology is referred to as DMC (Dynamic Motion Compensation), permitting a high precision "virtual platform" to be used for imaging and sounding. The primary design driver of SIAD is the 10 µrad accuracy performance requirement. 11)

The GOES Imager and GOES Sounder are collocated with SIAD on a common baseplate attached to the nadir panel. The SIAD instrument package consists of three star trackers (CT 602 by BATC) and a dual string HIRU (Hemispheric Inertial Reference Unit) package of Northrop Grumman. Attitude rates are being measured by HIRU, a 6-state Kalman filter, implemented in the spacecraft control processor, determines the spacecraft 3-axis attitude. The SIAD system is connected by the dual MIL-STD-1553 data bus. The star trackers feature a FOV of 8º x 8º, five stars may be tracked simultaneously. A simulation test analysis validated the functionality and performance of SIAD in 2001.

The ACS (Attitude Control Subsystem) of the GOES N-P series spacecraft consists of redundant microprocessor-based control electronics, sun sensors, Earth sensors, star trackers, gyros, reaction wheel assemblies (RWAs), a solar array drive (SAD), and an X-ray positioner (XRP) mechanism.

The nominal on-orbit attitude control operations are based on a zero momentum concept that provides precise pointing for the Imager and Sounder, communications service equipment, and scientific instruments. Bus control is accomplished by applying torque to internal RWAs (each wheel is capable of storing 75 Nms of momentum and of providing 0.2 Nm of reactive control torque). The SAD and XRP articulate the suite of scientific instruments mounted on the instrument mounting platform (IMP). Twelve 9.25 N bipropellant thrusters provide attitude control during orbit maneuvers. The ACS during transfer orbit is mostly passive with control applied only during re-orientations, spin speed changes, or liquid apogee motor (LAM) burns.

Parameter

GOES-I-M

GOES-N-P

GOES-R

Era

1994+

2006+

2015+

Navigation

112 µrad (day)
168 µrad (night)

65 µrad

28 µrad (1 km)

Frame-to-Frame
over 15 minutes

50 µrad (day)
70 µrad (night)

36 µrad

21 µrad

Frame-to-Frame
over 90 minutes

84 µrad (day)
105 µrad (night)

49 µrad

21 µrad

Table 3: Evolution of INR requirements

Legend to Table 3: All requirements are 3σ (99.7%) and apply to both East-West (EW) and North-South (NS) directions with relaxations under special circumstances. Distance equivalent at subsatellite point is 1 km = 28 µrad.

The INR system closes its control loop on the ground, as shown in Figure 3, with elements originally developed or evolved for GOES-N by Carr Astronautics and Integral Systems; comprising a:

• SPS (Sensor Processing System) that radiometrically calibrates image pixels, formats the GVAR (GOES Variable transmission format) product that is broadcast to the user community through the GOES spacecraft, conducts ranging through the GVAR link, and detects and measures stars when the instruments are in star-sense mode.

• RPM (Replacement Product Monitor) or simply PM that measures the locations of VIS and IR landmarks for orbit determination and INR quality control.

• OATS (Orbit and Attitude Tracking System) that estimates the orbit and attitude parameters for each instrument and creates IMC coefficient sets that are uploaded to the spacecraft.

• GOES NOP Telemetry and Command System (GTACS) that commands the spacecraft and identifies stars detected by the SPS according to the operational schedule.

• PES (Performance Evaluation System) that models the entire INR system and serves as a high fidelity design validation and implementation test tool.

The INR system closes one per day through the ground with the production of new sets of IMC coefficients that are then uploaded, enabled, and used for a period of 24 hours. There will nominally be one HK maneuver during any given 24-hour period and an eclipse period during eclipse season. IMC coefficient sets are produced for pre-maneuver and post-maneuver cases and special IMC sets are produced for eclipse periods. The DMC is generated in real-time onboard the spacecraft from the SIAD error signal. ISEC calibrations are infrequent and have not yet been applied.

GOES_NOP_AutoE

Figure 3: Functional block diagram of the INR system (image credit: NASA, Carr Astronautics Corp.)

The ACS (Attitude Control Subsystem) consists of redundant microprocessor-based control electronics, sun sensors, earth sensors, star trackers, gyros, RWAs (Reaction Wheel Assemblies), a SAD (Solar Array Drive), and an XRP (X-ray Positioner) mechanism. A block diagram of the ACS is shown in Figure 4.

Normal on-orbit attitude control operations are based on a zero momentum concept that provides precise pointing for the Imager and Sounder, communications service equipment, and scientific instruments. Bus control is accomplished by applying torque to internal RWAs. The SAD and XRP articulate the suite of scientific instruments mounted on the IMP (Instrument Mounting Platform). Twelve 9.25 N bipropellant thrusters provide attitude control during orbit maneuvers. The ACS during transfer orbit is mostly passive with control applied only during reorientations, spin speed changes, or LAM (Liquid Apogee Motor) burns.

GOES_NOP_AutoD

Figure 4: Block diagram of the ACS (image credit: NASA)

GOES_NOP_AutoC

Figure 5: Illustration of the GOES-N to P spacecraft (image credit: NASA, NOAA)

Some of the new top-level capabilities include: 12)

• A digital Low Rate Information Transmission (LRIT) formatted Weather Facsimile (WEFAX) service

• Expanded measurements for the Space Environment Monitor (SEM) instruments

• A new dedicated channel for the Emergency Managers Weather Information Network (EMWIN) service

• A more stable platform for supporting improved Imager, Sounder, and SXI instruments.

WEFAX to LRIT (Low-Rate Information Transmission) service conversion

LRIT is the next-generation "WEFAX system", a new transmission scheme to facilitate the efficient distribution of meteorological data from multiple international sources. WEFAX is the conventional system employed by NOAA and its user community, an analog meteorological broadcast service, to disseminate GOES data, POES data, as well as meteorological data from foreign agencies. The new digital formats of LRIT are intended to improve the quality, quantity, and availability of meteorological data from direct broadcast meteorological satellites, using a transmission service in L-band.

The CGMS (Coordination Group for Meteorological Satellites) is coordinating services for interoperability on a global scale. 13) 14)

• In 1991, a policy plan was recommended and initiated by all agencies concerned to replace the current WEFAX (Weather Facsimile) service with a more capable communication service on geostationary weather satellites

• At the CGMS meeting in 1998, a digital LRIT (Low-Rate Information Transmission) service concept was adopted by all participants (except NOAA)

• At the CGMS meeting in 1999, the US announced plans for LRIT on GOES I-M for January 2003

• At dual service transition period of about 2 years for WEFAX and LRIT is taking place in 2004 and 2005 (to cope with all issues involved in the transformation of existing ground systems and services). Transition (alternating transmissions of WEFAX and LRIT ) has begun with the current GOES East satellite (GOES-12) in the fall 2003 and with GOES West (GOES-10) in 2004, using an LRIT bandwidth of 128 kbit/s.

• NOAA plans call for LRIT service provision starting with GOES-N operations.

As of 1999, a global specification for Low Rate and High Rate Information Transmission (LRIT/HRIT) has been agreed to by all parties of CGMS. The specification bases on the CCSDS recommendations of Advanced Orbiting Systems (AOS) and the ISO standard 7498 (OSI Reference Model). It defines the structure and the formatting of the LRIT/HRIT files and the processing and the transport protocols of all OSI layers applicable to all geostationary meteorological spacecraft.

The LRIT service provides an allocated maximum bandwidth of 256 kbit/s.

RF communications: The GOES communications subsystem consists of the antennas and transponders that allow GOES to receive and transmit data. This includes raw instrument data transmitted to the ground, processed instrument data that is received on the spacecraft and then retransmitted to ground users, search and rescue data, weather data sent by the LRIT/WEFAX service, reports from the data collection platforms (DCPs), and the wide range of data transmitted by the EMWIN (Emergency Managers Weather Information Network).

The communication antennas on the spacecraft are mounted on the panel that faces the Earth. They send and receive data from the ground stations located within the GOES coverage area. Particular types of antennas, called L-band, S-band, and UHF (ultra-high frequency) antennas, provide communications for specific purposes. Some transmit data from the spacecraft to the ground (called downlink) while others transmit data from the ground to the spacecraft (uplink). For instance, an L-band antenna downlinks search and rescue data from the spacecraft to the ground while the UHF antenna receives search and rescue data and data from the DCPs. Additional antennas also receive data that is used to control the spacecraft and instruments.

The MDL (Multi-use Data Link) provides a medium-rate (400 kbit/s) downlink of Imager and Sounder servo error and Imager IMC data. The MDL also provides yoke and Imager/Sounder mounting surface angular displacement sensor data (all differential analog data digitized to 12 bits resolution). Also included are serially digitized SXI data, both spacecraft PCM telemetry streams, plus two analog spares for future use. The MDL processing and multiplexing function resides within the IRTCU (Instrument Remote Telemetry and Command Unit).

GOES_NOP_AutoB

Figure 6: Artist's rendition of the GOES N-P spacecraft (image credit: NASA, NOAA)


Launch: A launch of GOES-P took place on March 4, 2010 on a Delta-4 (4,2) expandable launch vehicle (using a 4 m fairing common booster core configuration with two solid strap-on motors) from Cape Canaveral, FLA, USA.

Orbit: Geostationary orbit at 75º W longitude (positioning into the "GOES East" location). Initial GTO after launch of 6,530 km x 35,000 km at 12º inclination with subsequent circularization of the orbit using a series of LAM (Liquid Apogee Motor) burns into GEO (35,786 km).

Coverage: GOES-East (slot at 75º W) provides the primary coverage of real-time weather information for North and South America and most of the Atlantic Ocean. The GOES-West (slot at 135º W) coverage region is mostly over the Pacific Ocean and North America. Total coverage of the system extends approximately from 20º W longitude to 165º E longitude. The main mission is carried out by the primary instruments, the Imager and the Sounder.

 


 

Operational status of GOES missions:

• Fall 2016: In geostationary orbit, NESDIS operates GOES-13 in the "GOES-East" position at 75° W and GOES-15 in the "GOES-West" position at 135° W. GOES-14 is available as an on-orbit spare, located at 105° W. NOAA's two operational GOES satellites provide consistent and reliable monitoring of the entire Western Hemisphere and are critical for identifying and tracking severe weather, snow storms, and tropical cyclones.

- GOES-East and GOES-West are providing data every 15 minutes to weather forecasters to support their forecasts and warnings. Although GOES-West experienced a component anomaly (i.e., loss of one of the two remaining star trackers) in April 2015, the satellite continues to operate on the single remaining star tracker and continues to meet all user performance requirements. The GOES-West Solar X-Ray Imager and X-Ray Sensor are acting as primary instruments, providing operational measurements, for NOAA's Space Weather Prediction Center. — In November 2015, the GOES-East sounder filter wheel stalled. However, the imager continues to operate normally and is meeting all essential NWS weather forecasting needs. The current on-orbit spare, GOES-14, is in normal configuration, instead of storage mode configuration, to provide quick services as a backup. GOES-14 has been periodically providing 1-minute Super Rapid Scan Operations to help algorithm developers, research partners, and forecasters prepare for the advanced capabilities available on the next-generation R-series geostationary satellites. All of the GOES-14 payload instruments are fully functioning without any performance degradation.

• On May 24, 2016, GOES-13 was 10 years on orbit. Known as GOES-N prior to launch, GOES-13 has been serving actively as GOES-East since April 2010. It was the first of NOAA's three-axis, body-stabilized geosynchronous environmental satellites and features a variety of enhanced instruments whose capabilities surpass those of earlier GOES satellites. Among them are: 15)

- An improved INR (Image Navigation and Registration) system that uses star trackers, optical devices that measures the position of the stars to help with spacecraft orientation, to provide more stable and accurate Earth-pointing capabilities, decreasing the amount of "shake" in an image.

- An imaging radiometer that uses data obtained from its five channels to continuously produce images of the Earth's surface, oceans, severe storm development, cloud cover, cloud temperature and height, surface temperature, and water vapor. It allows users to identify fog at night, distinguish between water and ice clouds during daytime hours, detect hot spots (such as volcanoes and forest fires), locate a hurricane eye, and acquire measurements of ground and sea surface temperatures.

- A sounder that provides detailed descriptions of conditions in the atmosphere at any time, allowing meteorologists to deduce atmospheric temperature and moisture profiles, surface and cloud-top temperatures, and ozone distributions. Sounder data is also used in computer models that produce mid-and long-range weather forecasts.

- A space environment monitor that consists of three components — an energetic particle sensor package, two magnetometer sensors, and a solar x-ray sensor — to keep tabs space weather conditions and provide warnings of geomagnetic storms capable of damaging communications and electrical infrastructure on Earth.

As part of the international COSPAS-Search and Rescue Satellite-Aided Tracking (SARSAT) system, GOES-13 carries a transponder that detects signals transmitted by 406 MHz emergency beacons used by planes, ocean-going vessels, and individuals in emergency situations and relays the location data to search and rescuers.

• GOES-15 is operational in 2015. In December 2011, GOES-15 was moved to 135ºW to replace GOES-11 as GOES-W.

• GOES-P (launch March 4, 2010): Twelve days after launch, GOES-P reached its geostationary orbit (from GTO) and was renamed to GOES-15. 16) 17)

- On April 6, 2010, GOES-15 captured its first visible image of Earth and on April 26, GOES-15 took its first full-disk infrared image.

- The SXI (Solar X-ray Imager) on GOES-15 suffered a voltage glitch soon after achieving orbit in the early checkout phase. This anomaly required the repair team of NASA, NOAA, and LMSAL engineers to persue all avenues to recover the instrument. On June 3, 2010, SXI finally came on-line. The team had subjected SXI to a series of long duration turn on tests in the hopes of clearing the short. About 16 hours into the testing, the instrument voltages returned to normal values and SXI now appears to be functioning properly. 18)

- GOES-15 will complete its checkout period in August 2010 and be stored on-orbit at 105º W, ready for activation should one of the operational GOES satellites degrade or exhaust their fuel.

GOES_NOP_AutoA

Figure 7: First image of the sun from the SXI instrument (image credit: NASA, NOAA, Lockheed Martin)

In 2010, the NOAA GOES system consists of: 19)

• GOES-13 became the official GOES-East satellite on April 14, 2010. GOES-13 was moved from on-orbit storage and into active duty. 20)

• In early Dec. 2009, NOAA deactivated GOES-10 after 12 years of service. The satellite was moved into a higher graveyard orbit. 21)

• GOES-10: In Dec. 2006 GOES-10 was positioned at 60º W longitude with an inclination of ~ 1º. Without the availability of station-keeping fuel, the inclination will continue to increase by about 0.95º per year. GOES-10 is providing regional coverage for South America and the Caribbean area. This represents a NOAA contribution to the EOPA (Earth Observation Partnership of the Americas) program on a best effort basis. 22)

NOAA replaced GOES-10 with GOES-11 as the operational GOES-W satellite in June of 2006 (135º W, inclination at 0.7º). However, GOES-10 is still functioning well, but has exhausted its north-south station-keeping fuel. GOES-10 completed its eastward drift from longitude 135º W to 60º W in early December 2006; it continues to operate as an XGOHI (Extended GOES High Inclination) satellite to provide coverage over South America. In Feb. 2009, the Sounder of GOES-10 stopped operating.

As the inclination rises, there are two effects that must be taken into account for operations. The first effect is the operational limit of the IMC (Image Motion Compensation) system. The current operating mode (IMC-On) entails small adjustment motions of the scan mirror to maintain the image-stability and co-registration. The limit of this system is approximately two degrees, which will be reached around July 2007. NOAA is in the process of developing a software enhancement to the Sensor Processing System (SPS) that will resample data taken in the IMC-Off mode to produce resampled GVAR (GOES Variable) data that appears (to the user) to be very similar to the IMC-On data we currently have and that can continue to be displayed by the current GVAR receiving systems.

• GOES-11: located at 135º W longitude and 0º inclination, is the operational West slot spacecraft. The SEM package is operating with degraded performance.

• GOES-12: located at 75º W longitude and 0º inclination, is the operational East slot spacecraft. The SEM package is operating with degraded performance. The SXI is not operational.

• The GOES-13 (formerly GOES-N) spacecraft, with a launch on May 24, 2006, was checked out after launch and placed in on-orbit storage on Jan. 5, 2007. GOES-13 is temporarily located at 105º W. It will remain in storage (standby) until either thruster fuel is depleted or instrument failure occurs on one of the two currently operational GOES satellites. As of June 2009, GOES-13 is still on orbit storage.

• The GOES-13 Imager and Sounder as well as the SXI instrument, transmitted their first images in Aug. 2006 when the checkout period started. GOES-13 met all of its INR requirements for normal operations during its checkout period.

• The GOES-14 spacecraft was placed into on-orbit storage in December 2009. The S/C was launched on June 27, 2009 and subsequently functionally tested and calibrated. NASA turned over the responsibility of the S/C to NOAA on Dec. 14, 2009. 23)

• For GOES-15, it will take ~ 5 months for all the instruments on board to be tested and calibrated. After that, GOES-15 will be a back-up satellite, stored on-orbit and ready for activation should one of the operational GOES satellites degrade or exhaust their fuel.

 


 

Sensor complement: (GOES Imager, GOES Sounder, SEM, XRS, SXI, DCS)

The sensor complement consists of government provided instruments to the prime contractor BSIS. The first three sets of Imagers and Sounders will be essentially the same as for the GOES I-M series. Imager channels remain the same as those on GOES-M, with a reduction in horizontal resolution from 8 km to 4 km in the 13.3 µm channel (TIR) on GOES-O and P. The Sounder instruments consist of the same filter-wheel based sounders as before.

 

GOES Imager:

The GOES Imager was designed and developed by ITT Industries Inc. (ITT-A/CD) of Fort Wayne, IN. The imager is a multispectral five-channel instrument that produces visible and infrared images of Earth's surface, oceans, cloud cover and severe storm developments. The Imager senses radiant energy and reflected solar energy from the Earth's surface and atmosphere. - The GOES-N/O/P Imagers will not have the 12-13 µm channel (a volcanic ash-sensitive channel which was converted to a cloud-sensing 13 - 13.7 µm channel on GOES-M). Note: GOES-O/P provides an improved 4 km resolution in the 13-13.7 µm channel. 24)

Band wavelength (µm)

Pixel size (km)

Primary objective of observations (products)

0.52 - 0.71 (VIS)

1 x 1

Daytime cloud cover

3.73 - 4.07 (MWIR)

4 x 4

Nighttime cloud cover

5.80 - 7.30 (MWIR)

4 x 4

Water vapor

10.20 - 11.20 (TIR)

4 x 4

Earth and cloud images; sea surface temperature and water vapor

13.00 - 13.70 (TIR)

8 x 8 on GOES-N;
4 x 4 on GOES-O&P

Cloud cover and cloud height

Table 4: Spectral band specification of the GOES Imager

The GOES Imager simultaneously senses emitted thermal and reflected solar energy from selected areas of the Earth. It uses a scan mirror system to alternately sweep east to west and west to east perpendicular to a north-to-south path. The rate of scanning allows the instrument to gather data in its five spectral bands while stepping north-to-south from a 3,000 km x 3,000 km target area in three minutes, and from a target area of 1,000 km x 1,000 km in just 41 seconds.

GOES_NOP_Auto9

Figure 8: Illustration of the GOES Imager instrument (image credit: NASA)

GOES_NOP_Auto8

Figure 9: Conceptual view of the target areas to be scanned by the GOES Imager (image credit: NASA, NOAA)

 

GOES Sounder:

The GOES Sounder was also designed and developed by ITT Industries Inc. The Sounder is a 19-channel discrete-filter radiometer, designed to sense the emitted thermal energy and reflected solar energy from sampled areas of the Earth's surface and atmosphere to provide data for computing vertical profiles of temperature and moisture, surface and cloud-top temperatures, and ozone distribution. The Sounder looks at conditions in "columns" of the atmosphere - cylindrical sections that extend from the Earth's surface to the upper reaches of the atmosphere.

The Sounder operates by means of a scan mirror that steps across the disk of the Earth in a west-to-east and east-to-west direction along a north-to-south path as the filter wheel rotates. The filter wheel has 18 filters, each of which corresponds to a particular band or wavelength in the electromagnetic spectrum. Each filter allows only energy with a particular wavelength to reach the detectors. All 18 filters and the visible band are sampled during each rotation, which occurs 10 times per second.

GOES_NOP_Auto7

Figure 10: Illustration of the GOES Sounder instrument (image credit: NASA)

Observation range

Channel No

Center wavelength (µm)

Objective

TIR (Thermal Infrared)
or longwave infrared

1
2
3
4
5
6
7
8
9

14.71
14.37
14.06
13.64
13.37
12.66
12.02
11.03
9.71

Temperature sounding
Temperature sounding
Temperature sounding
Temperature sounding
Temperature sounding
Temperature sounding
Surface temperature
Surface temperature
Total ozone

MWIR (Midwave Infrared)

10
11
12
13
14
15

7.43
7.02
6.51
4.57
4.52
4.45

Water vapor
Water vapor
Water vapor
Temperature sounding
Temperature sounding
Temperature sounding

SWIR (Shortwave Infrared)

16
17
18

4.13
3.98
3.74

Temperature sounding
Surface temperature
Surface temperature

VIS (visible)

19

0.70

Cloud detection

Figure 11: Spectral channel allocation of the GOES Sounder

Feature

GOES Imager

GOES Sounder

Optical aperture

31.1 cm

31.1 cm

Telescope type

Cassegrain

Cassegrain

Total step & sample time

N/A

0.1 s (0.2 s and 0.4 s optional)

Methods of scan

2-axis, continuous,
linear E-W, 64 µrad (2.3 km)
line step N-S, 224 µrad (8 km)

2-axis, step & dwell; E/W 280 µrad steps; N/S 1120 µrad steps (optional 2240 µrad steps, 0.2 s dwell)

Scan rate

20º/s optical

40 soundings/s

Slew rate

10º/s mechanical

10º/s mechanical

Spatial resolution (µrad)

VIS = 28, Ch. 2,4, & 5 = 112,
Ch. 3 = 224

all channels = 242 µrad (diameter)

Sampling

1.75/IGFOV VIS, Ch. 2, Ch. 4 & Ch. 5 3.5/IGFOV Ch. 3

4 IGFOVs sampled simultaneously

Sampling rate

183.3 µs/pixel (IR),
45.8 µs/pixel (VIS)

0.1 s

Chan. co-registration

± 28 µrad

Within 22 µrad of channel 8

Star sensing

Uses visible array SNR 6 for 4th mag stars (400 samples)

Separate visible array SNR 6 for 4th mag stars (each sample)

Data output

10 bit quantization

13 bit quantization

Data rate

2.6208 Mbit/s

40 kbit/s

Data format

NRZ-S, PN code

NRZ-S, PN code

Patch temperature

Regulated at 94 K, 101 K or 104 K

Regulated at 94 K, 101 K or 104 K

Time between space looks

2.2 s large frame
9.2 or 36.6 s smaller frame

2 min

Time between BB calibrations

10-30 min (can override or inhibit)

20 min (can override or inhibit)

Priority frame select

1 level normal; 2 levels priority
1 level star sense

1 level normal; 2 levels priority
1 level star sense

Table 5: GOES second generation instrument parameters

 

SEM (Space Environment Monitor):

The objective of the SEM package is to measure solar radiation in the X-ray and EUV (Extreme Ultraviolet) region and the in-situ magnetic field and energetic particle environment at geosynchronous orbit, providing real-time data to the NOAA(SEC (Space Environment Center). 25)

The SEM subsystem consists of multiple instruments used to monitor the near Earth (geostationary altitude) space environment and observe solar X-ray (XRS) and extreme ultraviolet (EUV) output.

- XRS/EUV instrument mounted on a positioning platform, fixed on the solar array yoke, observes solar output (measurement of disk-integrated solar X-ray and EUV fluxes).

- EPS (Energetic Particle Sensor) and the HEPAD (High Energy Proton and Alpha Detector) measure the flux of protons, alpha particles, and electrons over an extensive range of particle energies

- Two redundant three-axis magnetometers, mounted on a deployed 8.5 m boom, operate simultaneously to measure Earth's geomagnetic field strength and variations in the vicinity of the spacecraft.

GOES_NOP_Auto6

Figure 12: The SEM instrument suite (image credit: NASA, NOAA)

• The XRS/EUV sensor measures disk-integrated solar x-ray and EUV fluxes. The XRS/EUV consists of two channels in the X-ray sensor, five channels in the EUV sensor, and a DPU (Digital Processing Unit) that controls the instrument. The microprocessor based DPU supports both sensors, providing power, telemetry and command, and data processing (see Figure 14). The XRS design is based on an ion chamber design from previous (2nd generation) GOES spacecraft and the EUV sensor design is similar to one flown on the SOHO spacecraft. The sensor telescopes use magnetic shielding to reduce the background from high energy electrons, and the detectors are all well shielded from ambient particles and bremsstrahlung effect.

The XRS is an X-ray telescope that measures solar X-ray flux in two bands of 0.05 - 0.3 nm and 0.1- 0.8 nm. The XRS assembly consists of a telescope collimator, sweeper magnet assembly, dual ion chamber and preamplifier subassemblies. Two ion chambers detect X-rays, one chamber for each spectral range. The detector output signals are processed by separate electronic channels that have a single range in each band, with the >5 decade dynamic range logarithmically compressed into a 15 bit data word. Data transmitted through the spacecraft PCM telemetry permit real time ground determination of the solar X-ray emission in the two spectral bands.

The five-channel EUV telescope uses transmission gratings, filters, and solid state detectors to measure the extreme ultraviolet flux in five wavelength bands centered at 10 nm, 30 nm, 60 nm, 80 nm, and 126 nm respectively. The five EUV channels are mounted on three optical benches with channel pairs A-B and C-D sharing components such as gratings and front apertures. The A-B channel pair uses a 5000 line/mm transmission grating, and the C-D channel pair uses a 2500 line/mm transmission grating. The E channel uses a 1667 line/mm transmission grating and one Lyman Alpha Filter. A strong magnetic field sweeps out electrons below 4 MeV. Radiation shielding of detectors further reduces bremsstrahlung effects.

Spectral bands
XRS-A
XRS-B
EUV-A
EUV-B
EUV-C
EUV-D
EUV-E


0.05 - 0.3 nm
0.1 - 0.8 nm
5 - 15 nm
25 - 34 nm
20 - 65 nm
20 - 82 nm
119 - 127 nm

Threshold Sensitivity:
- Signal to noise ratio, 10 second interval


30

Resolution:
- XRS, fluxes >20 times threshold
- EUV


<2%
0.25%, full scale

Noise

Mean signal equal to the standard deviation of the data over a 10 s interval

Sampling rate:
- XRS
- EUV


Once every 2.048 s
Thrice every 32.768 s

Wavelength response

±5%

Angular response: (Sensitivity varies less than 5%)
- XRS
- EUV


29.1 arcmin
30.1 arcmin

Pointing determination accuracy with respect to sun center

±2 arcmin

Table 6: Performance summary of XRS/EUV

Threshold flux, dynamic range

Threshold Flux

Dynamic Range

XRS-A
XRS-B
EUV-A
EUV-B
EUV-C
EUV-D
EUV-E

5x10-9 W/m2
2x10-8 W/m2
1x10-6 W/m2
2x10-6 W/m2
1x10-6 W/m2
2x10-6 W/m2
1x10-4 W/m2

10,000
10.000
1,000
1,000
1,000
100
100

Table 7: Threshold values for XRS/EUV instrumentation

• The EPS/HEPAD instrument is partially based on the previous GOES EPS/HEPAD design for the measurement of medium and high energy protons, electrons, and alpha particles, that originate from the sun, are trapped in the magnetosphere, or are generated by cosmic rays deep in space. The complete EPS/HEPAD instrument consists of two energetic proton, electron, and alpha detectors (EPEADs), a magnetospheric proton detector (MAGPD), a magnetospheric electron detector (MAGED), a high energy proton and alpha detector (HEPAD), and a DPU that controls the five sensors and interfaces with the spacecraft.

GOES_NOP_Auto5

Figure 13: EPS/HEPAD instrument locations (image credit: NASA, NOAA)

GOES_NOP_Auto4

Figure 14: Illustration of the XRS/EUV/SXI assembly without harness and blankets (image credit: NASA, NOAA)

Particle

Channel

Range (MeV)

Sample time (s)

Proton
Proton
Proton
Alpha
Alpha
Alpha

P1
P2
P3
A1
A2
A3

0.74 - 4.2
4.2 - 8.7
8.7 - 14.5
3.8 - 9.9
9.9 - 20.5
20.5 - 61

8.2
32.8
32.8
32.8
32.8
32.8

Table 8: EPEAD telescope detector energy range

Particle

Channel

Range (MeV)

Sample time (s)

Proton
Proton
Proton
Proton
Alpha
Alpha
Alpha
Electron
Electron
Electron

P4
P5
P6
P7
A4
A5
A6
E1
E2
E3

15 - 40
38 - 82
84 - 200
110 - 900
60 - 160
160 - 260
330 - 500
> 0.6
> 2
> 4

32.8
32.8
32.8
32.8
32.8
32.8
32.8
4.1
16.4
16.4

Table 9: EPEAD dome detector energy range

MAGPD and MAGED: Magnetospheric protons and electrons are measured at nine pitch angle directions using two detector sets (MAGPD and MAGED). The detector sets are mounted on the anti-Earth side of the spacecraft and measure protons or electrons at 0º, ±35°, and ±70º from the anti-Earth direction in both the equatorial and the azimuthal plane. Each detector telescope has a full detection cone angle of 30º.

The MAGPD (Magnetospheric Proton Detector) measures protons in five differential energy channels from 80-800 keV and is based on the SEM-2 MEPED instrument on the NOAA polar orbiting operational environmental spacecraft (POES). The MAGPD telescopes each have two SSDs (Solid State Detectors) that operate in an anticoincidence mode to provide the required proton channels. Sweeping magnets exclude electrons below several hundred keV.

The MAGED (Magnetospheric Electron Detector) measures electrons in five differential energy channels from 30-600 keV and is also based on the SEM-2 MEPED instrument on the POES spacecraft. Physically, the MAGED is very similar to the MAGPD, the only difference being the detector assemblies. The MAGED telescopes each use a single SSD with a foil light shield and do not have sweeping magnets. Algorithms are provided to correct the electron channels for the proton contamination that is unavoidable with this detection system.

Channel

Range (keV)

Sample time (s)

MP1
MP2
MP3
MP4
MP5

80 - 100
110 - 170
170 - 250
250 - 350
350 - 800

16.4
16.4
16.4
32.8
32.8

Table 10: MAGPD detector energy range

Channel

Range (keV)

Sample time (s)

ME1
ME2
ME3
ME4
ME5

30 - 50
50 - 100
100 - 200
200 - 350
350 - 600

2.0
2.0
4.1
16.4
32.8

Table 11: MAGED detector energy range

HEPAD (High Energy Proton Alpha Detector) is based on the instrument on the previous GOES spacecraft but modified to provide channel count accumulation within the HEPAD unit. The HEPAD interfaces with the DPU, which controls the HEPAD and formats the accumulated counts and housekeeping data for spacecraft telemetry. The instrument uses two SSDs in a telescope arrangement with a Cerenkov radiator/photomultiplier tube (PMT) detector to measure relativistic protons and alpha particles. A triple coincidence among these three detectors sends a particle detection signal, and the PMT measures the energy. The HEPAD measures protons with energies above 330 MeV and alpha particles with energies above 2.56 GeV.

Particle

Channel

Range (MeV)

Sample time (s)

Proton
Proton
Proton
Proton
Alpha
Alpha
Detector D1
Detector D2
PMT
PMT
D1/D2 coincidence

P8
P9
P10
P11
A7
A8
S1
S2
S3
S4
S5

330 - 420
420 - 510
510 - 700
> 700
2560 - 3400
> 3400
Diagnostic
Diagnostic
Alpha lamp low
Alpha lamp low
Fast coincidence

32.8
32.8
32.8
32.8
32.8
32.8
4.1
4.1
4.1
4.1
4.1

Table 12: HEPAD detector energy range

Magnetometers: There are two magnetometers on the spacecraft. Each magnetometer consists of a triaxial fluxgate sensor and an electronics unit. Each magnetometer measures three orthogonal vector components of the magnetic field in the vicinity of the spacecraft. The three magnetometer axes are orthogonal to within ±0.5º and have a linear range of ±512 nanoTesla (nT). The determination of the ambient magnetic field in the vicinity of the spacecraft is continuous and simultaneous.

The two three-axis magnetometers provide redundancy for measuring the geomagnetic field. One magnetometer is mounted at the end of the boom 8.5 meters away (outboard) from the spacecraft, and the second, 0.8 meters inboard from the first on the same boom. These large distances from the spacecraft significantly reduce magnetic effects from the spacecraft body.

Dynamic range

±512 nT, ambient field in any orientation

Resolution

0.03 nT

Accuracy

< ±4 nT without temperature correction
< ±1 nT with temperature correction

Noise

≤ 0.3 nT, 3σ

Data rate

1.95 Hz

Bandwidth

0.5 Hz, 3 dB

Sensor axes orthogonality

Within ± 0.5º

Sensor orientation

≤ ±1.0º, in spacecraft coordinates (accuracy knowledge)

Spacecraft field contamination (max permanent field per axis)

± 100 nT

Sensor stability

±0.25º

Table 13: Magnetic field measurement performance parameters

 

SXI (Solar X-ray Imager) - part of the SEM package:

SXI (Solar X-ray Imager) was built by the Lockheed Martin Solar and Astrophysics Laboratory (LMSAL). The objective of SXI is to monitor the sun's X-rays for the early detection of solar flares. This early warning is important because these solar flares affect not only the safety of humans in high-altitude missions, such as the Space Shuttle, but also military and commercial satellite communications. 26) 27) 28)

The SXI instrument observes the sun in the soft X-rays broadband of 0.6-6.0 nm (or 6-60 Å). The instrument cannot be focused by transmissive optics or by "normal-incidence" mirrors. It is necessary to use grazing incidence mirrors, typically shaped like a cylinder, with the X-rays making one or more bounces at very shallow angles. The GOES-13 instrument uses a modified Wolter design with a single piece of glass fashioned into two sections. In a break with past designs, both sections have a hyperboloidal figure, which provides a flatter overall focus. Like all such optical systems, the GOES-N SXI design suffers from a geometric vignetting that increases linearly with displacement from image center. The magnitude of the vignetting approaches 13% for features lying 20 arcmin off-axis.

The SXI instrument employs thinned, back-illuminated CCD detectors. The detector provides a 5 arcsec pixel size and bandpasses of roughly 6 to 60 Å (corresponding to~0.2 to 2 keV). Image sequences are defined by sets of commandable tables.

The SXI CCD detector provides the following characteristics:

• 528 x 588 active pixel imaging area

• Back illuminated to maximize quantum efficiency in the low energy X-ray region

• 16 µm square pixels

• Anti blooming facility to improve the dynamic range by preventing charge spilling into adjacent pixels

• On-chip temperature sensors

• Two output amplifiers (for redundancy)

• Dump gate and drain for windowing.

The overall performance of the GOES-13 SXI is similar in spatial resolution to the Yohkoh SXT telescope in full-image mode. SXI provides continuous, near real-time observation of the sun's corona, acquiring a full-disk image every minute. The images cover a 42 arcmin FOV with five arcsec pixels.

Imaging exposure times:
- Solar flare sites
- Active regions
- Coronal loops
- Coronal hole boundaries


< 10 ms
< 100 ms
< 1 second
< 10 seconds

Spacecraft SXI boresight pointing (to center of solar disk)

Within 3 arcmin elevation, within 3.5 arcmin azimuth

FOV (Field of View)

42 arc min x 42 arcmin

Pixel size

5 arcsec x 5 arcsec, square pixels

Spectral sensitivity (integration time 100 ms)

 

Spectral band

Source

Minimum detectable photon radiance incident on the telescope entrance (photon cm-2 arcsec-2 sec-1)

6 to 20 Å
6 to 60 Å

Cu (13.3 Å)
C (44.7 Å)

85
112

Dynamic range

1000 when measured with monochromatic illumination at 44.7 Å

Telemetry amplitude digitization

12 bit (linear or logarithmic channels)

Enpixeled energy

13.3 Å (Cu)

44.7 Å

On axis

26%

29%

10 arcmin off axis

27%

32%

20 arcmin off axis

52%

52%

Resolution (on axis)

7 arcsec (full width half max)

SXI on-orbit useful life

3 years with a goal of 5 years (after 5 years ground storage)

Table 14: Parameters of the SXI instrument

GOES_NOP_Auto3

Figure 15: The SXI structural assembly (image credit: NOAA/SEC)

Telescope assembly: The telescope design consists of three basic groups: objective group, metering tube group, and focal plane group. The main components of the objective group are a hyperboloid-hyperboloid grazing incidence X-ray mirror, entrance filters, the HASS (High Accuracy Sun Sensor), and a mirror mounting structure. The metering tube group consists of a metering tube and its mount. The focal plane group components are a CCD detector, filter wheel assembly, and CCD radiator.

GOES_NOP_Auto2

Figure 16: The SXI telescope assembly (image credit: NASA)

The SXI instrument is housed in the yoke assembly of the GOES-N spacecraft, as shown in Figure 17. The main body of the spacecraft points continuously at Earth, but the yoke assembly on which the solar array panels are mounted counter-rotates to face the sun at all times.

The SXI telescope, along with other solar observing sensors, is mounted on an instrument mounting platform (IMP). The SXI is coaligned on the IMP with the combined XRS/EUV (X-ray Sensor and Extreme Ultraviolet Radiometer) and the PSS (Precision Sun Sensor). The IMP is mounted to the XRP (X-ray Positioner). The complete assembly including the XRP is called the XRS/EUV/SXI assembly (Figure 14).

The XRP is a single-axis gimbal aligned in the north-south direction, tracking the sun in solar declination. The solar array drive (SAD) assembly controls the east-west pointing of the yoke, tracking the diurnal motion of the sun. Both the XRP N-S pointing and the yoke E-W pointing are controlled during routine observations by spacecraft-provided closed-loop control systems utilizing the two-axes of the PSS as aspect sensors.

 

GOES_NOP_Auto1

Figure 17: Accommodation of the SXI instrument package on GOES-N. O, P (image credit: NOAA/SEC)

GOES_NOP_Auto0

Figure 18: Solar X-ray Imager and solar array in deployed configuration (image credit: NASA)

 

DCS (Data Collection System):

The DCS has been enhanced to support 300 and 1200 bit/s DCPs (Data Collection Platforms) using 8-PSK modulation and a higher power satellite transponder so that more DCPs can use the link at the same time. See description under 2nd generation GOES.

 


1) http://www.boeing.com/defense-space/space/bss/about/about_text.html

2) http://goes.gsfc.nasa.gov/text/goesnopq.status.html

3) Vanessa L. Griffin, "OSPO (Office of Satellite and Product Operations) COPC Brief, Spring 2016, URL: http://www.ofcm.gov/groups/COPC/meetings/2016-01/03-OSPO%20COPC%202016%20draft%20ver4.7.3.pdf

4) "GOES-N,O/P/Q - The Next Generation," NASA Brochure, NP-2001-7-324-GSFC, URL: http://goespoes.gsfc.nasa.gov/goes_npbooklet/booklet.pdf

5) http://goespoes.gsfc.nasa.gov/goes/spacecraft/index.html

6) http://www.boeing.com/defense-space/space/bss/factsheets/601/goes_nopq/goes_nopq.html

7) GOES-N DataBook, April 26, 2006, URL: http://goes.gsfc.nasa.gov/text/goes.databookn.html

8) "GOES N Data Book," Rev B, February 2005, Copyright © 2006 Boeing, URL: http://goes.gsfc.nasa.gov/text/GOES-N_Databook/databook.pdf

9) C. Carson, J. L. Carr, C. Sayal, "GOES-13 end-to-end INR performance verification and post-launch testing," 5th GOES Users' Conference, January 22-23, 2008, New Orleans, LA, USA (part of the 88th AMS Annual Meeting ), URL: http://ams.confex.com/ams/pdfpapers/135921.pdf

10) James L. Carr, Bruce Gibbs, Houria Madani, Nate Al len, "INR Performance of the GOES-13 Spacecraft Measured in Orbit," Proceedings of the AAS Guidance and Control Conference, Breckenridge, CO, USA, Feb. 1-6, 2008, AAS 08-077

11) Y. A. Wu, R. K. Li, A. D. Robertson, "Precision Attitude Determination for GOES-N Satellite," Proceedings of the 26th AAS Conference on Guidance and Control, Breckenridge, CO, Feb. 5-9, 2003, Vol. 113 Advances in the Astronautical Sciences, Edited by I. J. Gravseth and R. D. Culp, AAS 03-002, pp. 21-38

12) http://goespoes.gsfc.nasa.gov/goes/spacecraft/n_p_spacecraft.html

13) http://noaasis.noaa.gov/LRIT/

14) Active CGMS members are: EUMETSAT (Europe), JMA (Japan), CMA (China), HYDROMET (Russia), NOAA (USA), and WMO. The global network of meteorological satellites constitutes a major portion of the space-based GOS (Global Observing System) of WWW (World Weather Watch).

15) "GOES-13 Turns 10," NESDIS News Archive, May 24, 2016, URL: http://www.nesdis.noaa.gov/news_archives/goes_13.html

16) "NASA and NOAA's Environmental Satellite Now GOES-15," March 19, 2010, URL: http://www.nasa.gov/centers/goddard/news/releases/2010/10-029.html

17) http://www.nasa.gov/mission_pages/GOES-P/main/index.html

18) "GOES-15 Solar X-Ray Imager's Miraculous First Light," June 14, 2010, URL: http://www.nasa.gov/mission_pages/GOES-P/news/xray_imager.html

19) http://www.oso.noaa.gov/goesstatus/

20) "GOES-13 is America's New GOES-EAST Satellite," NASA, April 16, 2010, URL: http://www.nasa.gov/mission_pages/goes-n/media/goes-east.html

21) "NOAA Deactivates GOES-10 After 12 Years Of Tracking Storms," Space Mart, Dec. 7, 2009, URL: http://www.spacemart.com/reports/NOAA_Deactivates_GOES_10_After_12_Years-Of_Tracking_Storms_999.html

22) "XGOHI, eXtended GOES High Inclination Mission," April 4, 2007, URL: http://www.oso.noaa.gov/seminars/docs/XGOHI-Presentation-04-04-07.pdf

23) "GOES-14 (O) Moving into On-Orbit Storage Around the Earth," NASA, Nov. 30, 2009, URL: http://www.nasa.gov/mission_pages/GOES-O/news/orbit_storage.html

24) http://goes.gsfc.nasa.gov/text/GOES-N_Databook/section03.pdf

25) http://goes.gsfc.nasa.gov/text/GOES-N_Databook/section05.pdf

26) http://www.lockheedmartin.com/news/press_releases/2005/LOCKHEEDMARTIN-SOLARXRAYIMAGERBELAUN.html

27) "Solar X-Ray Imager," Feb. 2005, URL: .http://rsd.gsfc.nasa.gov/goes/text/GOES-N_Databook/section06.pdf

28) http://www.mssl.ucl.ac.uk/www_detector/sxi/SXIintro.html
 


The information compiled and edited in this article was provided by Herbert J. Kramer from his documentation of: "Observation of the Earth and Its Environment: Survey of Missions and Sensors" (Springer Verlag) as well as many other sources after the publication of the 4th edition in 2002. - Comments and corrections to this article are always welcome for further updates (herb.kramer@gmx.net).

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