![]() An artist's concept of C/NOFS satellite | |
Names | Communications/Navigation Outage Forecasting System |
---|---|
Mission type | Technology demonstration |
Operator | STP / AFRL |
COSPAR ID | 2008-017A |
SATCAT no. | 32765 |
Mission duration | 3 years (planned) 7.5 years (achieved) |
Spacecraft properties | |
Manufacturer | General Dynamics |
Launch mass | 384 kg (847 lb) [1] |
Start of mission | |
Launch date | 16 April 2008, 17:02:48 UTC |
Rocket | Pegasus-XL (F39) |
Launch site | Bucholz, Stargazer, Runway 6/24 |
Contractor | Orbital Sciences Corporation |
End of mission | |
Decay date | 28 November 2015 |
Orbital parameters | |
Reference system | Geocentric orbit [2] |
Regime | Low Earth orbit |
Perigee altitude | 405 km (252 mi) |
Apogee altitude | 853 km (530 mi) |
Inclination | 13.00° |
Period | 97.30 minutes |
Instruments | |
C/NOFS Occultation Receiver for Ionospheric Sensing and Specification (CORISS) Coherent Electromagnetic Radio Tomography (CERTO) Coupled Ion-Neutral Dynamics Investigation (CINDI) Planar Langmuir Probe (PLP) Vector Electric Field Instrument (VEFI) | |
Explorer program |
C/NOFS, or Communications/Navigation Outage Forecasting System was a USAF satellite developed by the Air Force Research Laboratory (AFRL) Space Vehicles Directorate to investigate and forecast scintillations in the Earth's ionosphere. It was launched by an Orbital Sciences Corporation Pegasus-XL launch vehicle at 17:02:48 UTC on 16 April 2008 and decayed on 28 November 2015.
The satellite, which was operated by the Space Test Program (STP), allowed the U.S. military to predict the effects of ionospheric activity on signals from communication and navigation satellites, outages of which could potentially cause problems in battlefield situations.
C/NOFS had a three-axis stabilization system equipped with seven sensors. It was placed into low Earth orbit with an orbital inclination of 13.00°, a perigee of 405 km (252 mi) and an apogee of 853 km (530 mi). [2] It carried the CINDI experiment for NASA. Launch had been scheduled for 2003, but was delayed for a number of reasons.
The spacecraft payload consists of the following instruments:
The C/NOFS Occultation Receiver for Ionospheric Sensing and Specification (CORISS) is a Global Positioning System (GPS) dual-frequency receiver that measures the total electron content (TEC) along the line-of-sight from C/NOFS to GPS satellite. TEC measurement can help to constrain C/NOFS ionospheric models. Limb profiles of TEC obtained during occultations can be inverted to produce vertical profiles of electron density. It may be also possible to measure L-band scintillations caused by electron density irregularities. [3]
The Coherent Electromagnetic Radio Tomography (CERTO) is a tri-band (150, 400, 1067 MHz) radio beacon that permits direct measurement of ionospheric scintillation parameters at several frequencies by ground receivers. CERTO measurements can also be used for tomographic reconstruction of electron density profiles. [4]
The Coupled Ion-Neutral Dynamics Investigation (CINDI) payload is funded by NASA as an Explorer Mission of Opportunity. CINDI consists of two instruments: the Ion Velocity Meter (IVM) and the Neutral Wind Meter (NWM). The IVM instrument includes an ion drift meter and a retarding potential analyzer. IVM measure the ion drift vector, the ion temperature, and the major ion composition with a spatial resolution of about 4 km (2.5 mi) along the satellite track; the ion drift meter also provides vertical and horizontal ion drift components at 500 m (1,600 ft) resolution. The NWM consists of a cross track wind sensor and a ram wind sensor providing a direct measure of the neutral wind vector with a spatial resolution of about 8 km (5.0 mi) along the satellite track. [5]
The Planar Langmuir Probe (PLP) is a dual-disk probe designed to provide in situ measurements of plasma density and density fluctuations. Low time-resolution density measurements are intended as inputs for background ionosphere models and high time-resolution density irregularity measurements to specify disturbance conditions. PLP also monitors the spacecraft surface potential. [6]
The Vector Electric Field Instrument (VEFI) consists primarily of three orthogonal 20 m (66 ft) tip-to-tip double probe antennas. It measures the alternating current (AC) and Direct current (DC) electric fields related to plasma drift and irregularity development. The VEFI instrument package also includes a fluxgate magnetometer, an optical lightning detector and a fixed-bias Langmuir probe. [7]
C/NOFS science data is available online for general use. VEFI and PLP data are available through NASA Goddard's Coordinated Data Analysis Web. [8] CINDI data are available through the William B. Hanson Center for Space Science [9] at the University of Texas at Dallas.
![]() An artist's concept of C/NOFS satellite | |
Names | Communications/Navigation Outage Forecasting System |
---|---|
Mission type | Technology demonstration |
Operator | STP / AFRL |
COSPAR ID | 2008-017A |
SATCAT no. | 32765 |
Mission duration | 3 years (planned) 7.5 years (achieved) |
Spacecraft properties | |
Manufacturer | General Dynamics |
Launch mass | 384 kg (847 lb) [1] |
Start of mission | |
Launch date | 16 April 2008, 17:02:48 UTC |
Rocket | Pegasus-XL (F39) |
Launch site | Bucholz, Stargazer, Runway 6/24 |
Contractor | Orbital Sciences Corporation |
End of mission | |
Decay date | 28 November 2015 |
Orbital parameters | |
Reference system | Geocentric orbit [2] |
Regime | Low Earth orbit |
Perigee altitude | 405 km (252 mi) |
Apogee altitude | 853 km (530 mi) |
Inclination | 13.00° |
Period | 97.30 minutes |
Instruments | |
C/NOFS Occultation Receiver for Ionospheric Sensing and Specification (CORISS) Coherent Electromagnetic Radio Tomography (CERTO) Coupled Ion-Neutral Dynamics Investigation (CINDI) Planar Langmuir Probe (PLP) Vector Electric Field Instrument (VEFI) | |
Explorer program |
C/NOFS, or Communications/Navigation Outage Forecasting System was a USAF satellite developed by the Air Force Research Laboratory (AFRL) Space Vehicles Directorate to investigate and forecast scintillations in the Earth's ionosphere. It was launched by an Orbital Sciences Corporation Pegasus-XL launch vehicle at 17:02:48 UTC on 16 April 2008 and decayed on 28 November 2015.
The satellite, which was operated by the Space Test Program (STP), allowed the U.S. military to predict the effects of ionospheric activity on signals from communication and navigation satellites, outages of which could potentially cause problems in battlefield situations.
C/NOFS had a three-axis stabilization system equipped with seven sensors. It was placed into low Earth orbit with an orbital inclination of 13.00°, a perigee of 405 km (252 mi) and an apogee of 853 km (530 mi). [2] It carried the CINDI experiment for NASA. Launch had been scheduled for 2003, but was delayed for a number of reasons.
The spacecraft payload consists of the following instruments:
The C/NOFS Occultation Receiver for Ionospheric Sensing and Specification (CORISS) is a Global Positioning System (GPS) dual-frequency receiver that measures the total electron content (TEC) along the line-of-sight from C/NOFS to GPS satellite. TEC measurement can help to constrain C/NOFS ionospheric models. Limb profiles of TEC obtained during occultations can be inverted to produce vertical profiles of electron density. It may be also possible to measure L-band scintillations caused by electron density irregularities. [3]
The Coherent Electromagnetic Radio Tomography (CERTO) is a tri-band (150, 400, 1067 MHz) radio beacon that permits direct measurement of ionospheric scintillation parameters at several frequencies by ground receivers. CERTO measurements can also be used for tomographic reconstruction of electron density profiles. [4]
The Coupled Ion-Neutral Dynamics Investigation (CINDI) payload is funded by NASA as an Explorer Mission of Opportunity. CINDI consists of two instruments: the Ion Velocity Meter (IVM) and the Neutral Wind Meter (NWM). The IVM instrument includes an ion drift meter and a retarding potential analyzer. IVM measure the ion drift vector, the ion temperature, and the major ion composition with a spatial resolution of about 4 km (2.5 mi) along the satellite track; the ion drift meter also provides vertical and horizontal ion drift components at 500 m (1,600 ft) resolution. The NWM consists of a cross track wind sensor and a ram wind sensor providing a direct measure of the neutral wind vector with a spatial resolution of about 8 km (5.0 mi) along the satellite track. [5]
The Planar Langmuir Probe (PLP) is a dual-disk probe designed to provide in situ measurements of plasma density and density fluctuations. Low time-resolution density measurements are intended as inputs for background ionosphere models and high time-resolution density irregularity measurements to specify disturbance conditions. PLP also monitors the spacecraft surface potential. [6]
The Vector Electric Field Instrument (VEFI) consists primarily of three orthogonal 20 m (66 ft) tip-to-tip double probe antennas. It measures the alternating current (AC) and Direct current (DC) electric fields related to plasma drift and irregularity development. The VEFI instrument package also includes a fluxgate magnetometer, an optical lightning detector and a fixed-bias Langmuir probe. [7]
C/NOFS science data is available online for general use. VEFI and PLP data are available through NASA Goddard's Coordinated Data Analysis Web. [8] CINDI data are available through the William B. Hanson Center for Space Science [9] at the University of Texas at Dallas.