The Tiny Remote-sensing Instrument for Thermospheric Oxygen and Nitrogen (TRITON) is being developed by the U.S. Naval Research Laboratory (NRL) for detection of neutral components of the daytime thermosphere. TRITON measures naturally occurring, far ultraviolet (FUV) emissions of the upper atmosphere that are produced as a result of solar excitation. The sensor concept is based primarily on multiple sensors previously developed at NRL with recent spaceflight heritage. The legacy optics have been under evaluation and development for extension to new emission targets and brighter ambient environments. Recent TRITON development work has included characterization of a new photomultiplier tube and comparison to performance of a previously used model. In addition, several bandpass filters are evaluated for their effectiveness in providing the out-of-band rejection needed to isolate the FUV and MUV emissions of interest. The primary optical layout of TRITON sensors will be described to highlight the components that have been changed or adapted for use in the new configuration. The results of recent lab tests will also be shown to demonstrate the expected performance of TRITON relative to prior, legacy components and subsystems.
Metal atoms and ions are deposited into the Earth’s Upper Atmosphere and Ionosphere via meteor ablation. The neutral atoms can undergo charge exchange with extant O+, O2+, and N2+ ions to become metallic ions. Metallic ions have lifetimes of several days in the ionosphere, allowing vertical wind shear to compress them into thin, dense layers that subsequently produce Sporadic-E propagation of HF radio signals. The Triple Magnesium Ionospheric Photometer (Tri-MIP) instrument was developed by the US Naval Research Laboratory (NRL) to observe airglow emissions from magnesium ions (Mg+) in the Earth’s atmosphere and measure global-scale Mg+ density from orbit as a proxy for the metallic ion population. This CubeSat compatible Space Weather sensor is a 1U ionospheric photometer that observes the ultraviolet 280 nm fluorescent emission of Mg+ on the sunlit portion of the orbit. The primary objective is to characterize the Mg+ distribution in the Earth’s atmosphere. We present the Tri-MIP instrument concept, laboratory measurements, and upcoming mission concepts.
The second generation Tiny Ionospheric Photometer (TIP) is a compact, high-sensitivity, nighttime ionospheric photometer designed for small satellites. TIP launched February 19, 2017 to the International Space Station as part of the GPS Radio Occultation and Ultraviolet Photometry—Colocated (GROUP-C) experiment to test advanced sensing objectives. The TIP optical design improves upon previously-flown photometers and employs a filter wheel to measure signals. The third generation sensor is a 1U Cubesat-compatible Triple Tiny Ionospheric Photometer (Tri-TIP), manifested to fly on the dual 6U Coordinated Ionospheric Reconstruction CubeSat Experiment (CIRCE) in early 2020. The Tri-TIP design builds upon several technologies demonstrated aboard TIP, but utilizes a beam splitter to simultaneously monitor signal, red-leak, and background signals. This paper compares the pre-flight and on-orbit performance of TIP with pre-test theoretical results for Tri-TIP.
The Coordinated Ionospheric Reconstruction Cubesat Experiment (CIRCE) is a joint US/UK mission consisting of two 6U CubeSats actively maintaining a lead-follow configuration in the same low Earth orbit with a launch planned for the 2020 timeframe. These nanosatellites will each feature multiple space weather payloads. From the US, the Naval Research Laboratory will provide two 1U Triple Tiny Ionospheric Photometers (Tri-TIPs) on each satellite, observing the ultraviolet 135.6 nm emission of atomic oxygen at nighttime. The primary objective is to characterize the twodimensional distribution of electrons in the Equatorial Ionization Anomaly (EIA). The methodology used to reconstruct the nighttime ionosphere employs continuous UV photometry from four distinct viewing angles in combination with an additional data source, such as in situ plasma density measurements, with advanced image space reconstruction algorithm tomography techniques. From the UK, the Defence Science and Technology Laboratory (Dstl) is providing the In-situ and Remote Ionospheric Sensing suite consisting of an Ion/Neutral Mass Spectrometer, a triple-frequency GPS receiver for ionospheric sensing, and a radiation environment monitor. We present our mission concept, simulations illustrating the imaging capability of the Tri-TIP sensor suite, and a range of science questions addressable via these measurements.
The U.S. Naval Research Laboratory (NRL) has developed the Triple Tiny Ionospheric Photometer (Tri-TIP), an ultraviolet remote-sensing instrument based on the TIP. Tri-TIP measures emissions of atomic oxygen (Oi 135.6 nm) to determine plasma density in the nighttime ionosphere. The Tri-TIP design shrinks TIP to a 1U CubeSat form-factor and simplifies the mechanical design with a three-channel photometer system to isolate the target wavelength without a filter wheel. A heated strontium fluoride (SrF2) filter eliminates incoming light at wavelengths shorter than 135.6 nm. The filtered light is divided between two matched photometers by a beam splitter with a magnesium fluoride coating over aluminum (AlMgF2) deposited on 50% of the surface in a polka-dot pattern. The third photometer monitors dark count noise for later subtraction. One Tri-TIP configuration uses a beam splitter with a sapphire (Al2O3) substrate, which is opaque to wavelengths shorter than ∼140 nm, to later subtract contaminating emissions at wavelengths longer than 140 nm. A second Tri-TIP configuration uses a MgF2 substrate beam splitter to simultaneously measure Oi 135.6 nm from two adjacent fields-of-view. The performance of both beam splitters has been tested at NRL, and the results are presented.
We have developed the Triple Tiny Ionospheric Photometer (Tri-TIP) as a CubeSat-compatible 1U sensor to obtain high-sensitivity measurements of the far-ultraviolet (FUV) OI 1356 Å airglow for remote sensing of ionospheric density. The Tri-TIP concept evolved from heritage sensors flown on the COSMIC/FORMOSAT-3 (CF3) constellation, and more recently as part of the GPS and Radio Occultation and UV Photometry – Colocated (GROUP-C) experiment on the International Space Station. The concept for all of these sensors is to isolate this emission using heated strontium-fluoride filters to eliminate shorter wavelength emissions such as O I 1304 Å and H I 1216 Å and cesium iodide photocathodes to reduce sensitivity longward of ~1800 Å. There are no other spectral features in this FUV portion of the airglow spectrum at night. However, the nadir-viewing sensors on CF3 observed significant long-wavelength emissions from city lights and moonlit clouds that contaminated the data. The GROUP-C instrument included a sapphire filter that could be alternated with the strontium fluoride to measure and remove this spectral “red leak” from the observations. The Tri-TIP design pairs a heated strontium fluoride filter in line with a sapphire beam splitter that feeds the UV (with spectral leak) and long-wavelength (spectral leak only) signals to two matched photomultiplier tubes (PMTs). A third PMT monitors the signal contribution from high-energy particles and dark current. We present the results from laboratory tests of these components that ensure the high-sensitivity performance of this new optical configuration for ionospheric remote sensing and imaging from a CubeSat platform.
The Coordinated Ionospheric Reconstruction Cubesat Experiment (CIRCE) is a dual-satellite mission consisting of two 6U CubeSats actively maintaining a lead-follow configuration in the same orbit with a launch planned for the 2018-2019 time-frame. These nanosatellites will each feature two 1U size ultraviolet photometers, observing the 135.6 nm emission of atomic oxygen at nighttime. The primary objective is to characterize the two-dimensional distribution of electrons in the orbital plane of the vehicles with special emphasis on studying the morphology of the Equatorial Ionization Anomaly (EIA). The methodology used to reconstruct the nighttime ionosphere employs continuous UV photometry from four distinct viewing angles in combination with an additional data source, such as in situ plasma density measurements or a wide-band beacon data, with advanced image space reconstruction algorithm tomography techniques. The COSMIC/FORMOSAT-3 (CF3) constellation featured six Tiny Ionospheric Photometers, compact UV sensors which served as the pathfinder for the CIRCE instruments. The TIP instruments on the CF3 satellites demonstrated detection of ionospheric bubbles before they had penetrated the peak of the F-region ionosphere, showed the temporal evolution of the EIA, and observed a Medium Scale Travelling Ionospheric Disturbance. We present our mission concept, some pertinent information regarding the instrument design, the results of simulations illustrating the imaging capability of the sensor suite, and a range of science questions addressable using such a system.
The SSULI (Special Sensor Ultraviolet Limb Imager) is a limb-scanning far- and extreme-ultraviolet spectrometer flying on the Defense Meteorological Satellite Program (DMSP). The sensor sensitivity is tracked through the mission life by taking advantage of serendipitous stellar apparitions which, over the course of several days, track across the sensor’s field of view, allowing for not only the production of a sensitivity curve when compared against the known stellar spectra, but additionally pointing information and field-of-view information can be gleaned from comparing the star’s expected and observed positions. Most notably, because the star’s apparition traces across the field of view predictably in one axis, and randomly in another, multiple apparitions of these point sources can be used to map out the gain on the detector’s entire surface, revealing the existence and extent of localized gain sags. Additionally, multiple, routinized, and scheduled calibrations can be used to track sensor behavior through the mission life, including effects like a detector scrub, photocathode performance, and possible optics contamination. Results from the SSULI 002/DMSP F18 and SSULI 005/DMSP F19 stellar calibrations are presented.
The Winds-Ions-Neutral Composition Suite (WINCS) instrument, also known as the Small Wind and Temperature Spectrometer (SWATS), was designed and developed jointly by the Naval Research Laboratory (NRL) and NASA/Goddard Space Flight Center (GSFC) for ionosphere-thermosphere investigations in orbit between 120 and 550 km altitude. The WINCS instrument houses four spectrometers in a single package with size, weight, and power compatible with a CubeSat. These spectrometers provide the following measurements: neutral winds, neutral temperature, neutral density, neutral composition, ion drifts, ion temperature, ion density and ion composition. The instrument is currently operating on the International Space Station and on the STP-Sat3 spacecraft. Data from the Ion-Drift Temperature-Spectrometer (IDTS) are used to compute the ion drift, temperature, and density in the presence of large changes in spacecraft potential. A summary is given of future flight manifests.
The SSULI (Special Sensor Ultraviolet Limb Imager) is a low-resolution hyperspectral far and extreme ultraviolet limb-scanning
imager designed to monitor ionospheric and thermospheric airglow. SSULI has a spectral range from 80 to 170
nm, and a nominal resolution of 2.1 nm (at 147 nm). The instrument is scheduled to fly aboard all Defense
Meteorological Satellite Program (DMSP) Block 5D3 weather satellites. The first SSULI instrument was launched in
fall 2003, aboard the DMSP F16 flight, and has been collecting data since December 2003. The second SSULI flight
aboard DMSP F17 began in fall 2006. Early in the missions, both instruments began to observe intermittent but
significant periods of noise across the entire instrument passband, beyond the expected ion noise associated with sub-auroral
latitudes and the South Atlantic Anomaly. The morphology and intensity of the noise correlates strongly with
environmental conditions such as spacecraft potential. In order for the ground processing software to extract individual
emission features from the measured spectra, the data must be filtered for quality and the noise must be characterized on
short time scales and introduced as additional basis functions for use with the Multiple Linear Regression (MLR) feature
extraction algorithm. New algorithms, in the form of an Ion Noise Filter, have been developed for use with the MLR.
The techniques used in the Ion Noise Filter are discussed and examples of the successful extraction of spectra are
demonstrated.
The SSULI (Special Sensor Ultraviolet Limb Imager) is a low-resolution hyperspectral far- and extreme-ultraviolet
limb-scanning imager designed to monitor ionospheric and thermospheric airglow. SSULI has a spectral range from 80
to 170 nm, and a nominal resolution of 2.1 nm (at 147 nm). The instrument is scheduled to fly aboard all DMSP Block
5D3 weather satellites. The first SSULI instrument was launched in fall 2003, aboard DMSP F16, and has been
collecting data since December 2003. The second SSULI flight aboard DMSP F17 began in fall 2006. On the ground,
the SSULI instruments are calibrated using a monochromator to isolate single emission features of interest produced by
a gas discharge lamp, whereas the flight spectra consists of numerous overlapping emissions. The determination of
individual emission feature contribution against the entire airglow spectrum is determined using the multiple linear
regression technique with basis functions defining each observable emission. The accuracy of the emission extraction
depends primarily on the ability to model the characteristics of the instrument line-shape, encompassing both optical
and electronic effects. In the course of developing the ground calibration algorithms, we are now able to produce line-shapes
much more faithful to the observed calibration features, as well as model instrument characteristics such as
scattered light and detector background components. This improved instrument characterization can then be passed to
the operational orbital emission extraction software to increase the fidelity of retrieved altitude profiles for observed
ultraviolet emissions. In addition, the techniques used with the ground calibration can monitor deviations in line-shape
and instrument sensitivity as a function of observed count rate, and these modified line-shapes can also be passed to the
ground analysis software. Validation of this method using SSULI 003 and 004 ground calibration data will be
presented.
The first of five Special Sensor Ultraviolet Limb Imager (SSULI) sensors was launched on the Defense Meteorological Satellite Program (DMSP) F16 spacecraft in October of 2003 into a sun-synchronous 830 km circular orbit at a local time of 0800-2000 UT. During initial sensor turn-on and evaluation, unusually high levels of background events were observed by the detector. The severity of this background is often sufficient to exceed the counting limit of the electronics as well as contribute to a rapid decrease in detector performance. In light of the SSULI performance degradation and concerns that the subsequent sensors may be affected in a similar manner, a "Tiger Team" investigation was launched to determine the source of the anomalous events. The conclusion from the investigation attributes the observed anomalous events to high levels of non-photon noise caused by ambient ions entering the instrument and striking the front microchannel plate. Additionally, the team made recommendations to mitigate the problem on future flights.
The Atmospheric Neutral Density Experiment (ANDE) is a series of four microsatellites that will study the atmosphere of the Earth from low earth orbit. Each microsatellite is based on a common design; however, each differs in the instrument payloads and the associated science and mission requirements. The primary mission objective is to provide total neutral density along the orbit for improved orbit determination of resident space objects. Each ANDE microsatellite has several secondary goals. It is the unique design of the microsatellites that allows this task to be accomplished.
Each microsatellite is a compact, near perfect sphere; this reduces shape and drag errors so that the local density of the atmosphere can be determined by instantaneous tracking variations detected by very high accuracy laser and radar ranging whereby the spacecrafts themselves are the primary sensing instrument. The accuracy of the atmospheric density measurements inferred from the orbital tracking of ANDE microsatellites will be much greater than that achieved by similar experiments in the past or from any currently proposed.
Many unique design challenges had to be overcome to achieve the necessary science, mission, and operational requirements as well as severe cost constraints. New methods for parts and assembly fabrication were sought out and implemented. These new methods allowed similar parts to function in each of the microsatellites despite the differences between them. In addition, the command and telemetry links used inexpensive COTS Ham radio transceivers while meeting all the International requirements for operations in the Amateur Satellite Service.
The Atmospheric Neutral Density Experiment (ANDE) is a low cost mission proposed by the Naval Research Laboratory to demonstrate a method to monitor the thermospheric neutral density at an altitude of 400 km. The primary mission objective is to provide total neutral density along the orbit for improved orbit determination of resident space objects. The ANDE mission also serves as a test platform for a new space-to-ground optical communications technique, the Modulating Retro-reflector Array in Space (MODRAS) experiment. Both are sponsored in part by the Department of Defense Space Test Program.
The mission consists of two spherical spacecraft fitted with retro-reflectors for satellite laser ranging (SLR). One spacecraft is completely passive; the other carries three active instruments; a miniature Wind And Temperature Spectrometer (WATS) to measure atmospheric composition, cross-track winds and neutral temperature; a Global Positioning Sensor (GPS); and a Thermal Monitoring System (TMS) to monitor the temperature of the sphere. A design requirement of the active satellite is to telemeter the data to the ground without external protrusions from the spherical spacecraft (i.e. an antenna). The active satellite will be fitted with the MODRAS system, which is an enabling technology for the ANDE mission. The MODRAS system consists of a set of multiple quantum well (MQW) modulating retro-reflectors coupled with an electronics package, which will telemeter data to the ground by modulating the reflected light from laser interrogation beam.
This paper presents a mission overview and emphasis will be placed on the design, optical layout, performance, ground station, and science capabilities of the combined missions.
The Atmospheric Neutral Density Experiment (ANDE) is a mission proposed by the Naval Research laboratory to monitor the thermospheric neutral density at an altitude of 400km. The mission objectives are to provide total neutral density along the orbit for improved orbit determination of resident space objects. The measurements also provide a critical validation point for the upcoming Special Sensor Ultraviolet Limb Imagers (SSULI) to be launched on each of the five Defense Meteorological Satellite Program (DMSP) spacecraft in block 5D3 starting in 2001. In addition ANDE provides two calibration objects for use in the Air Force High Accuracy Satellite Drag Model (HASDM) initiative to help maintain and improve accuracy of the space object catalog. The mission consists of two spherical satellites fitted with retro-reflectors for satellite laser ranging (SLR). One satellite is completely passive, the other carries active instrumentation to measure the partial pressure of atmospheric constituents, GPS positioning, acceleration in all 3 axes, and surface temperature. The active satellite will be fitted with modulating retro-reflectors. The spacecraft telemetry will be transferred to the ground by modulating and reflecting the SLR laser interrogation beam.
The Volumetric Imaging System for the Ionosphere (VISION) is designed to use limb and nadir images to reconstruct the three-dimensional distribution of electrons over a 1000 km wide by 500 km high slab beneath the satellite with 10 km x 10 km x 10 km voxels. The primary goal of the VISION is to map and monitor global and mesoscale (> 10 km) electron density structures, such as the Appleton anomalies and field-aligned irregularity structures. The VISION consists of three UV limb imagers, two UV nadir imagers, a dual frequency Global Positioning System (GPS) receiver, and a coherently emitting three frequency radio beacon. The limb imagers will observe the O II 83.4 nm line (daytime electron density), O I 135.6 nm line (nighttime electron density and daytime O density), and the N2 Lyman-Birge-Hopfield (LBH) bands near 143.0 nm (daytime N2 density). The nadir imagers will observe the O I 135.6 nm line (nighttime electron density and daytime O density) and the N2 LBH bands near 143.0 nm (daytime N2 density). The GPS receiver will monitor the total electron content between the satellite containing the VISION and the GPS constellation. The three frequency radio beacon will be used with ground-based receiver chains to perform computerized radio tomography below the satellite containing the VISION. The measurements made using the two radio frequency instruments will be used to validate the VISION UV measurements.
We present the concept for an instrument designed to map and monitor the ionosphere from geostationary orbit. This instrument will be used to study the spatial and temporal behavior of mesoscale (> 10 km) ionospheric structures. The instrument is designed to primarily operate at night as irregularities are generally more prevalent during the evening. The instrument will be sensitive enough to gather a high signal-to-noise image viewing the nadir in approximately 100 seconds. The instrument can also be operated as a limb imager. The instrument will image a 1.6 degree(s) field-of-view with 10 km spatial resolution. The experiment will use a two-axis gimbal to point to various points on the limb and disk of the Earth. The instrument consists of an extreme ultraviolet (EUV) imager and a far-ultraviolet (FUV) imager. The EUV imager will operate at 83.4 nm using a low resolution imaging spectrograph to set the passband. The O II 83.4 nm emission is produced by photoionization of O during the daytime. Above the limb, this emission can be used to determine altitude distribution of the O+ density. The FUV imager will operate at 130.4 , 135.6, and 143.0 nm. At night, The O I 130.4 and O I 135.6 nm emissions are produced by primarily by radiative recombination, and therefore these emissions provide useful ionospheric diagnostics at night. During the daytime, the 130.4 and 135.6 nm lines are primarily produced by photoelectron impact excitation of O; however the 130.4 nm line is also excited by resonant scattering of sunlight. The O I 130.4 and 135.6 nm lines provide information on the O density during the daytime. The instrument will map the daytime N2 column density using the Lyman-Birge-Hopfield bands near 143.0 nm.
The Advanced Research and Global Observation Satellite (ARGOS) has been operating since February 1999 and includes three spectrographs comprising the High Resolution Airglow and Auroral Spectroscopy (HIRAAS) experiment. The HIRAAS instruments remotely sense the Earth's mid-, far- and extreme-ultraviolet airglow to study the density, composition, and temperature of the thermosphere and ionosphere. The Low Resolution Airglow and Aurora Spectrograph (LORAAS) is a limb scanner covering the 80-170 passband nm with 1.8 nm spectral resolution. Repeated serendipitous observations of hot O- and B-type stars have been used to improve the aspect solution, characterize the instrument field-of-view, and monitor relative sensitivity degradation of the instrument during the mission. We present the methodology of performance characterization and report the observed performance degradation of the LORAAS wedge-and-strip microchannel plate detector. The methods and results herein can be utilized directly in on-orbit characterization of the SSULI operational sensors to fly aboard the DMSP Block 5D3 satellites.
The Naval Research Laboratory has built give Special Sensor Ultraviolet Limb Imagers (SSULIs) for the Defense Meteorological Satellite Program. These sensors are designed to measure vertical intensity profiles of the Earth's airglow in the extreme and far ultraviolet (800 to 1700 angstroms). The data from these sensors will be used to infer altitude profiles of ion, electron and neutral density. The first SSULI is scheduled to launch in 2000. An identical copy of the SSULI sensor called LORAAS was launched aboard the ARGOS spacecraft on February 23, 1999. Data from LORAAS will be used to verify the performance of the SSULI sensors, ground analysis software and validate the UV remote sensing technique. Together with the LORAAS instrument the SSULI program will collect data on the composition of the upper atmosphere for a complete solar cycle.
THe resolution and sensitivity of the special sensor UV limb imager (SSULI) spectrograph depend strongly on the quality of the detector. As a result, the Naval Research Laboratory (NRL) has given high priority to the refurbishment of a damaged detector and tow spares to evaluate possible improvements to the overall capabilities of the SSULI sensor. The goal of the detector refurbishment is to improve the detector imaging quality, counting efficiency, resolution, background uniformity, long term vacuum storage, and serviceability. Estimated improvement sin the sensor performance will be used to determine the feasibility of refurbishing all the remaining detectors and spectrographs. The NRL is currently refurbishing a SSULI detector. The completion of the detector refurbishment includes a detailed analysis of the detector performance. This paper describes the performance of the refurbished SSULI detector and a comparison tot he original detectors. Included is a detailed description of the testing methods and result as well as the impact to the performance of the SSULI spectrograph. The test that will be reported are counting efficiency, image uniformity and quality, gain variability, background uniformity, and anode alignment.
The Special Sensor Ultraviolet Limb Imager (SSULI) program involves the development of a series of five ultraviolet limb imaging spectrographs by the Naval Research Laboratory for the Defense Meteorological Satellite Program. In addition, a duplicate sixth instrument, the Low Resolution Airglow/Aurora Spectrograph (LORAAS) will be flown aboard the Space Test Program ARGOS satellite in late 1997. These instruments will measure vertical intensity profiles of the Earth's airglow in the extreme and far ultraviolet (800 to 1700 angstroms) with 19 angstroms resolution. The instruments view the limb using a rotating mirror to scan the 0.1 degree(s) X 2.4 degree(s) field of view from 750 km to 50 km tangent altitude. SSULI measurements will be used to infer altitude profiles of ion, electron and neutral density. The first SSULI is scheduled to launch in 2000, and coverage from all the instruments will provide a continuous atmospheric data set spanning an entire solar cycle. The first four SSULI instruments are complete, and detailed optical calibrations have been performed. Assembly and calibration of the remaining SSULI instrument and LORAAS are underway, and preliminary results are available. Preliminary results of the first SSULI instrument were reported in 1994. This paper updates the calibration results of the first instrument and presents a summary of the results of the next three SSULI instruments. Comparison between instrument characteristics are also discussed, including variations in calibration techniques. A brief discussion on the periodic calibration verification of the SSULI instruments during storage and prior to launch is included.
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