Harri Latvakoski

Wide-field Infrared Survey Explorer science payload update

The Wide Field Infrared Survey Explorer is a NASA Medium Class Explorer mission to perform a high-sensitivity, high resolution, all-sky survey in four infrared wavelength bands. The science payload is a 40 cm aperture cryogenically cooled infrared telescope with four 10242 infrared focal plane arrays covering from 2.8 to 26 μm. Mercury cadmium telluride (MCT) detectors are used for the 3.3 μm and 4.6 μm channels, and Si:As detectors are used for the 12 μm and 23 μm wavelength channels. A cryogenic scan mirror freezes the field of view on the sky over the 9.9-second frame integration time. A two-stage solid hydrogen cryostat provides cooling to temperatures less than 17 K and 8.3 K at the telescope and Si:As focal planes, respectively. The science payload collects continuous data on orbit for the seven-month baseline mission with a goal to support a year-long mission, if possible. As of the writing of this paper, the payload subassemblies are complete, and the payload has begun integration and test. This paper provides a payload overview and discusses instrument status and performance.

Far-infrared spectroscopy of the troposphere (FIRST): sensor development and performance drivers

The radiative balance of the troposphere, and hence global climate, is dominated by the infrared absorption and emission of water vapor, particularly at far-infrared (far-IR) wavelengths from 15-50 μm. Water vapor is the principle absorber and emitter in this region. The distribution of water vapor and associated far-IR radiative forcings and feedbacks are widely recognized as major uncertainties in our understanding of current and the prediction of future climate. Cirrus clouds modulate the outgoing longwave radiation (OLR) in the far-IR, and up to half of the OLR from the Earth occurs beyond 15.4 μm (650 cm-1). Current and planned operational and research satellites observe the mid-infrared to only about 15.4 μm, leaving space or airborne spectral measurement of the far-IR region unsupported. NASA is now developing the technology required to make regular far-IR measurements of the Earth’s atmosphere possible. Far InfraRed Spectroscopy of the Troposphere (FIRST) is being developed for NASA’s Instrument Incubator Program under the direction of the Langley Research Center. The objective of FIRST is to provide a balloon-based demonstration of the key technologies required for a space-based sensor. We discuss the FIRST Fourier transform spectrometer system (0.6 cm-1 unapodized resolution), along with radiometric calibration techniques in the spectral range from 10 to 100 μm (1000 to 100 cm-1). FIRST will incorporate a broad bandpass beamsplitter, a cooled (~180 K) high throughput optical system, and an image type detector system. The FIRST performance goal is a NEΔT of 0.2 K from 10 to 100 μm.

Far-infrared spectroscopy of the troposphere: instrument description and calibration performance

The far-infrared spectroscopy of the troposphere (FIRST) instrument is a Fourier transform spectrometer developed to measure the Earths thermal emission spectrum with a particular emphasis on far-infrared (far-IR) wavelengths greater than 15 μm. FIRST was developed under NASAs Instrument Incubator Program to demonstrate technology for providing measurements from 10 to 100 μm (1000 to 100 cm(-1)) on a single focal plane with a spectral resolution finer than 1 cm(-1). Presently no spectrometers in orbit are capable of directly observing the Earths far-IR spectrum. This fact, coupled with the fundamental importance of the far-IR to Earths climate system, provided the impetus for the development of FIRST. In this paper the FIRST instrument is described and results of a detailed absolute laboratory calibration are presented. Specific channels in FIRST are shown to be accurate in the far-IR to better than 0.3 K at 270 K scene temperature, 0.5 K at 247 K, and 1 K at 225 K.

A high-accuracy blackbody for CLARREO

The NASA climate science mission Climate Absolute Radiance and Refractivity Observatory (CLARREO), which is to measure Earths emitted spectral radiance from orbit for 5 years, has an absolute accuracy requirement of 0.1 K (3σ) at 220 K over most of the thermal infrared. To meet this requirement, CLARREO needs highly accurate on-board blackbodies which remain accurate over the life of the mission. Space Dynamics Laboratory is developing a prototype blackbody that demonstrates the ability to meet the needs of CLARREO. This prototype is based on a blackbody design currently in use, which is relatively simple to build, was developed for use on the ground or on-orbit, and is readily scalable for aperture size and required performance. We expect the CLARREO prototype to have emissivity of ~0.9999 from 1.5 to 50 μm, temperature uncertainties of ~25 mK (3σ), and radiance uncertainties of ~10 mK due to temperature gradients. The high emissivity and low thermal gradient uncertainties are achieved through cavity design, while the SItraceable temperature uncertainty is attained through the use of phase change materials (mercury, gallium, and water) in the blackbody. Blackbody temperature sensor calibration is maintained over time by comparing sensor readings to the known melt temperatures of these materials, which are observed by heating through their melt points. Since blackbody emissivity can potentially change over time due to changes in surface emissivity (especially for an on-orbit blackbody) an on-board means of detecting emissivity change is desired. The prototype blackbody will include an emissivity monitor based on a quantum cascade laser to demonstrate the concept.

Far infrared spectroscopy of the troposphere (FIRST): flight performance and data processing

The radiative balance of the troposphere, and hence global climate, is dominated by the infrared absorption and emission of water vapor, particularly at far-infrared (far-IR) wavelengths from 15-50 μm. Current and planned satellites observe the infrared region to about 15.4 μm, ignoring spectral measurement of the far-IR region from 15 to 100μm. The far-infrared spectroscopy of the troposphere (FIRST) project, flown in June 2005, provided a balloon-based demonstration of the two key technologies required for a space-based far-IR spectral sensor. We discuss the FIRST Fourier transform spectrometer system (0.6 cm-1 unapodized resolution), its radiometric calibration in the spectral range from 10 to 100 μm, and its performance and science data from the flight. Two primary and two secondary goals are given and data presented to show the goals were achieved by the FIRST flight.

Observational study: microgravity testing of a phase-change reference on the International Space Station

Background:Orbital sensors to monitor global climate change during the next decade require low-drift rates for onboard thermometry, which is currently unattainable without on-orbit recalibration. Phase-change materials (PCMs), such as those that make up the ITS-90 standard, are seen as the most reliable references on the ground and could be good candidates for orbital recalibration. Space Dynamics Lab (SDL) has been developing miniaturized phase-change references capable of deployment on an orbital blackbody for nearly a decade.Aims:Improvement of orbital temperature measurements for long duration earth observing and remote sensing.Methods:To determine whether and how microgravity will affect the phase transitions, SDL conducted experiments with ITS-90 standard material (gallium, Ga) on the International Space Station (ISS) and compared the phase-change temperature with earth-based measurements. The miniature on-orbit thermal reference (MOTR) experiment launched to the ISS in November 2013 on Soyuz TMA-11M with the Expedition 38 crew and returned to Kazakhstan in March 2014 on the Soyuz TMA-10 spacecraft.Results:MOTR tested melts and freezes of Ga using repeated 6-h cycles. Melt cycles obtained on the ground before and after launch were compared with those obtained on the ISS.Conclusions:To within a few mK uncertainty, no significant difference between the melt temperature of Ga at 1 g and in microgravity was observed.

Far-infrared Spectroscopy of the Troposphere (FIRST): sensor calibration performance

The radiative balance of the troposphere, and hence global climate, is dominated by the infrared absorption and emission of water vapor, particularly at far-infrared (far-IR) wavelengths from 15-50 μm. Water vapor is the principal absorber and emitter in this region. The distribution of water vapor and associated far-IR radiative forcings and feedbacks are widely recognized as major uncertainties in our understanding of current and the prediction of future climate. Cirrus clouds modulate the outgoing longwave radiation (OLR) in the far-IR. Up to half of the OLR from the Earth occurs beyond 15.4 μm (650 cm-1). Current and planned operational and research satellites observe the midinfrared to only about 15.4 μm, leaving space or airborne spectral measurement of the far-IR region unsupported. NASA has now developed the sensor required to make regular far-IR measurements of the Earths atmosphere possible. Far InfraRed Spectroscopy of the Troposphere (FIRST) was developed for NASAs Instrument Incubator Program under the direction of the Langley Research Center. The objective of FIRST is to provide a balloon-based demonstration of the key technologies required for a space-based sensor. The FIRST payload will also be proposed for science flights in support of validation of the various experiments on the Earth Observing System (EOS). We discuss the FIRST Fourier transform spectrometer system (0.6 cm-1 unapodized resolution), along with its radiometric calibration in the spectral range from 10 to 100 µm (1000 to 100 cm-1). FIRST incorporates a broad bandpass beamsplitter, a cooled (~180 K) high throughput optical system, and an image type detector system. We also discuss the actual performance of the FIRST instrument relative to its performance goal of a NE(delta)T of 0.2 K from 10 to 100 μm.

Characterization of a quantum cascade laser-based emissivity monitor for CORSAIR

Continuous improvements of quantum cascade laser (QCL) technology have extended the applications in environmental trace gas monitoring, mid-infrared spectroscopy in medicine and life science, law enforcement and homeland security and satellite sensor systems. We present the QCL based emissivity monitor for the CORSAIR blackbody. The emissivity of the blackbody was designed to be better than 0.9999 for the spectral range between 5 to 50μm. To actively monitor changes in blackbody emissivity we employ a QCL-based infrared illumination source. The illumination source consisted of a QCL and thermoelectric cooler (TEC) unit mounted on a copper fixture. The stability of the QCL was measured for 30, 60, and 90s operation time at 1.5A driving current. The temperature distribution along the laser mounting fixture and time dependent system heat dispersion were analyzed. The results were compared to radiative and conductive heat transfer models to define the potential laser operating time and required waiting time to return to initial temperature of the laser mount. The observed cooling behaviour is consistent with a primarily conductive heat transfer mechanism.

Characterization of a Quantum Cascade Laser Based Emissivity Monitor for CORSAIR

The QCL based emissivity monitor which was designed to obtain emissivity uncertainty goal of ±0.00015 (3σ) for the CORSAIR blackbody has been characterized. The laser power stability and temperature distribution of the system are analyzed.

Pre-launch characterization of the WISE payload

The Wide-field Infrared Survey Explorer (WISE), launched on December 14, 2009, is a NASA-funded Explorer mission that is providing an all-sky survey in the mid-infrared with far greater sensitivity and resolution than any previous IR survey mission. The WISE science payload is a cryogenically cooled infrared telescope with four 1024x1024 infrared focal plane arrays covering from 2.8 to 26 μm, which was designed, fabricated, and characterized by Utah State Universitys Space Dynamics Laboratory. Pre-launch charaterization included measuring focus, repeatability, response non-linearity, saturation, latency, absolute response, flatfield, point response function, scanner linearity, and relative spectral response. We will provide a brief overview of the payload, discuss the overall characterization approach, review several pre-launch characterization methods in detail, and present selected results from ground characterization and early on-orbit performance.