More sophisticated non-dispersive infrared (NDIR) sensors for gas analysis have been developed in recent years, with many references in the literature. This technique is one of the most cost-effective methods to quantify the concentration of a target gas by measuring its absorption of infrared radiation. Dual channel thermopiles comprised of target and reference filter channels are reliably used to monitor the target gas for NDIR sensors. In recent years, commercial off-the-shelf quad-channel thermopiles with integrated passband infrared absorption filters have become available and enable up to three gas mixture detection and quantification, but there is no truly parallel readout circuit available for signal post processing. These sensors with their high sensitivity, fast response time and no cooling requirement makes them ideal candidates for applications that require monitoring multiple gases in real time. Usually, an NDIR sensor uses a cost-effective micro-controller for signal post processing, this limits the monitoring of multiple gases to a serial readout architecture. In this paper, we present a proof-of-concept non-dispersive infrared-red (NDIR) gas analyzer that has been realized with a quad-channel thermopile and a parallel readout circuitry consisting of a multi-channel digitizer (MCD) application specific integrated circuit (ASIC) and a field programmable gate array (FPGA). The parallel readout architecture will help considerably in the calibration schema. The NDIR gas analyzer will be used in a future space-based instrument application to ensure the safe transfer of sublimated volatiles from a comet sample containment system to a gas containment system within the operational pressure-temperature condition.
Planetary science exploration is transitioning from a focus on remote sensing techniques to in situ instruments for landed missions, and Raman spectrometers are quickly gaining ground as essential to these payloads. To accurately identify targets of interest to planetary science, the Raman spectrometer spectral resolution is required to be better than 0.19 nm. While dispersive spectrometers are a direct way to separate optical radiation into its constituent irradiance spectrum, they have major disadvantage of very inefficient light throughput for high resolution applications because they require very small entrances slits, ~50 μm. This is a major drawback for a stand-off system where target sample illumination size is large and return signals are very weak. Fluorescence is typically brighter than the Raman signal, and in conventional Raman spectroscopy, a slow detector integrates both signals and obscures the Raman signature. To mitigate this, we are developing an ultra-compact, high resolution, high throughput, time-resolved VIS-NIR Raman spatial heterodyne spectrometer (SHS). The SHS replaces the modulation mirror in a high resolution and throughput of a traditional Fourier Transform Spectrometer (FTS) with a stationary grating. The SHS has the same advantage of the FTS, which has two orders of magnitude larger acceptance angle than dispersive spectrometers without sacrificing resolution. In this work we focus on applications to stand-off Raman SHS spectroscopy for the detection of biomarkers and characterization of habitability on planetary surfaces.
With the rapid advancement of imaging technology, space-based remote sensing instruments are becoming more sophisticated and are producing substantially more amounts of data for downloading. Data alteration is very likely to occur during the transmission over the long distances from probes to carrier spacecraft and subsequently back to Earth,. Cyclic Redundancy Check (CRC) is the most well-known data package error check technique which has been used in many applications. Unfortunately, due to its serial computation process, it could be a bottleneck for critical applications that require rapid processing. To overcome such issue, we present here a parallel CRC computational method based on an FPGA with simulation and testing to validate the methodology.
Optical designs for the next generation space science instruments call for unconventional, aspheric, and freeform (FF), prescriptions with tight tolerances. These advanced surfaces enable superior-performance, compact, and lower cost systems but are more challenging to characterize and, hence, to fabricate and integrate. A method was developed to characterize a wide range of optical surfaces, without requiring custom-made correctors, and to align them to each other for a high-performance optical system. A precision coordinate measuring machine, equipped with a non-contact, chromatic confocal probe, was used to measure numerous optics including large convex conics, high-sloped aspherics, several FF surfaces, and grazing-incidence x-ray optics. The resulting data were successfully reduced using custom-developed, advanced surface fitting analysis tool, to determine the optic’s alignment relative to the global and local coordinate systems, surface departure from design, and the as-built optical prescription. This information guided the modeling and the alignment of the corresponding as-built optical systems, including a flight system composed of a three-mirror anastigmat.
Lunar Ice Cube, scheduled to be launched on ARTEMIS I in late 2021, is a deep space cubesat mission with the goals of demonstrating 1) a cubesat-scale instrument (BIRCHES) capable of addressing NASA HEOMD Strategic Knowledge Gaps related to lunar volatile distribution (abundance, location, and transportation physics of water ice), and 2) cubesat propulsion, via the Busek BIT 3 RF Ion engine. The mission will also demonstrate the AIM/IRIS microcryocooler for the first time in deep space. BIRCHES integration is nearly complete, with several changes made to the thermal design to improve detector performance. Final preflight instrument testing and calibration, our ongoing concern to be emphasized here, have been delayed due to the mandated closure rules of NASA facilities. Lunar Ice Cube, along with two other cubesats deployed from ARTEMIS I, Lunar Flashlight and LunaH-Map, will be the first deep cubesat missions to deliver science data to the Planetary Data System.
NASA Goddard Space Flight Center (GSFC) has successfully developed and tested a custom-designed low-noise multi-channel digitizer (MCD) application specific integrated circuit (ASIC) for operation in harsh radiation environments. The MCD-ASIC is optimized for low-frequency and low-voltage signal measurements from sensors and transducers. It has 20 input channels where each channel is comprised of auto-zeroed chopper variable-gain amplifier, post amplifier, and a second order ΣΔ modulator. ΣΔ analog-to-digital converter (ADC) relies on oversampling and noise shaping to achieve high-resolution conversion. However, the MCD-ASIC requires digital filtering and decimation to convert the output single bit streams from the ADC to useful data words. A parallel digital platform such as a field-programmable-gate-array (FPGA) is highly suitable to fully leverage the capabilities of the MCD-ASIC. The FPGA controls the MCD-ASIC via serial peripheral interface (SPI) protocol and acquires data from it. A Python-script communicates with the FPGA board through a USB interface on a cross operating platform. Using this architecture, the system is capable of monitoring up to 20 voltage readout channels simultaneously in a real-time manner. Each channel’s parameters can be programmed independently allowing maximum user versatility. In this paper, we present analysis of the analog front-end, the implementation of the digital processing unit on the FPGA, and provide noise performance results from the MCD-ASIC readout.
A proof-of-concept, compact, portable Fourier Ptychographic Microscope (FPM) to perform wide field-of-view, high spatial resolution imaging (<1 μm) for biosignature motility in liquid samples, is presented. The FPM has the potential method to be developed as a space-based payload for future landers destined to the Ocean Worlds. A portable FPM using an existing Fourier ptychography (FP) algorithm adapted for reconstruction is demonstrated. A NVIDIA Jetson Nano board and camera combined with FP, is used to computationally reconstruct sub-micron resolution images. Additionally, deep learning was employed to perform inferencing prediction which enables the on-edge FPM device.
Pamela Clark, Tilak Hewagama, Shahid Aslam, James Bauer, Michael Daly, Lori Feaga, Dave Folta, Nicolas Gorius, Kyle Hughes, Terry Hurford, Donald Jennings, Timothy Livengood, Michael Mumma, Conor Nixon, Jessica Sunshine, Geronimo Villanueva, Kevin Brown, Ben Malphrus, Aaron Zucherman
Here we describe the Primitive Object Volatile Explorer (PrOVE), a smallsat mission concept to study the surface structure and volatile inventory of comets in their perihelion passage phase when volatile activity is near peak. CubeSat infrastructure imposes limits on propulsion systems, which are compounded by sensitivity to the spacecraft disposal state from the launch platform and potential launch delays. We propose circumventing launch platform complications by using waypoints in space to park a deep space SmallSat or CubeSat while awaiting the opportunity to enter a trajectory to flyby a suitable target. In our Planetary Science Deep Space SmallSat Studies (PSDS3) project, we investigated scientific goals, waypoint options, potential concept of operations (ConOps) for periodic and new comets, spacecraft bus infrastructure requirements, launch platforms, and mission operations and phases. Our payload would include two low-risk instruments: a visible image (VisCAM) for 5-10 m resolution surface maps; and a highly versatile multispectral Comet CAMera (ComCAM) will measure 1) H2O, CO2, CO, and organics non-thermal fluorescence signatures in the 2-5 μm MWIR, and 2) 7-10 and 8-14 μm thermal (LWIR) emission. This payload would return unique data not obtainable from ground-based telescopes and complement data from Earth-orbiting observatories. Thus, the PrOVE mission would (1) acquire visible surface maps, (2) investigate chemical heterogeneity of a comet nucleus by quantifying volatile species abundance and changes with solar insolation, (3) map the spatial distribution of volatiles and determine any variations, and (4) determine the frequency and distribution of outbursts.
Several classes of planetary science observations require high spatial resolution in UV and visible wavelengths. Key examples include (a) the detection of satellites and characterization of their orbits, (b) the discovery of faint and small objects among the NEO, asteroid, Kuiper belt or Sedna-like populations and (c) cloud or trace gas observations in planetary atmospheres. Hubble Space Telescope (HST) observations have been very productive in these areas: consider the recent discovery of Makemake's satellite (Parker et al., 2016), the discovery of 2014 MU69 (now the flyby target of the New Horizons spacecraft) or the OPAL (Outer Planet Atmospheres Legacy) program.
Like HST, large-aperture ground-based telescopes with adaptive optics can also achieve spatial resolutions of 50 mas, but normally at wavelengths longer than ~1 μm. Projects like MagAO-2K are working on improving image quality at visible wavelengths, but while the core PSF (Point Spread Function) width might be narrow (projected to be 15 mas at the Magellan telescope), the Strehl ratio drops steeply with wavelength (Males et al., 2016). Not all science goals suffer equally from low Strehl ratios, however: cloud tracking on Venus is more tolerant of a low Strehl ratio than searching for a close satellite of Makemake.
A telescope on a NASA super-pressure balloon would float above 99.3% of the atmosphere, where the inner Fried parameter is thought to be two meters or more. While atmospheric turbulence is not expected to impact image quality, there are other sources of wavefront error (WFE), such as mirror figuring, misalignment of the OTA (Optical Telescope Assembly) or asymmetric heating from the Sun or Earth. We reference recent work that estimates balloon telescope WFEs from different sources to generate a suite of plausible PSFs. We apply these PSFs to the UV and visible wavelength science cases outlined in the GHAPS/SIDT report (Gondola for High Altitude Planetary Science/Science Instrument Definition Team). We quantify the impact that WFE has on achieving the planetary observations outlined in the SIDT report.
Balloon based telescopes represent an opportunity to observe science in an environment with almost no atmospheric effects. However, balloon based platforms include a wide range of thermal environments as well as pointing a lightweight telescope over a large elevation range. The Gondola for High Altitude Planetary Science (GHAPS) was designed to provide nearly diffraction limited performance observations over the visible and infrared spectrum with a 1- meter aperture. To achieve such performance, detailed Structural Thermal Optical Performance (STOP) was used to predict telescope performance. Software was built to automate the process of analysis, enabling thermal, structural and optical analyses to be executed quickly with less effort. The end result was the capability to analyze both generic operating conditions and Design Reference Mission conditions, producing predictions that could be used to evaluate the quality of science return.
Gas Abundance Sensor Package (GASP) is a stand-alone scientific instrument that has the capability to measure the concentration of target gases based on a non-dispersive infrared sensor system along with atmospheric reference parameters. The main objective of this work is to develop a GASP system which takes advantage of available technologies and off-the-shelf components to provide a cost-effective solution for localized sampling of gas concentrations. GASP will enable scientists to study the atmosphere and will identify the conditions of the target’s planetary local environment. Moreover, due to a recent trend of miniaturization of electronic components and thermopiles detectors, a small size and robust instrument with a reduction in power consumption is developed in this work. This allows GASP to be easily integrated into a variety of small space vehicles such as CubeSats or small satellite system, especially the Micro-Reentry Capsule (MIRCA) prototype vehicle. This prototype is one of the most advanced concepts of small satellites that has the capability to survive the rapid dive into the atmosphere of a planet. In this paper, a fully-operational instrument system will be developed and tested in the laboratory environment as well as flight preparation for a field test of the instrument suite will be described.
The space based mission Pegase was proposed to CNES in the framework of its call for scientific proposals for formation
flying missions. This paper presents a summary of the phase-0 performed in 2005. The main scientific goal is the
spectroscopy of hot Jupiters (Pegasides) and brown dwarfs from 2.5 to 5 μm. The mission can extend to other objectives
such as the exploration of the inner part of protoplanetary disks, the study of dust clouds around AGN,... The instrument
is basically a two-aperture (D=40 cm) interferometer composed of three satellites, two siderostats and one beam-combiner.
The formation is linear and orbits around L2, pointing in the anti-solar direction within a +/-30° cone. The
baseline is adjustable from 50 to 500 m in both nulling and visibility measurement modes. The angular resolution ranges
from 1 to 20 mas and the spectral resolution is 60. In the nulling mode, a 2.5 nm rms stability of the optical path
difference (OPD) and a pointing stability of 30 mas rms impose a two level control architecture. It combines control
loops implemented at satellite level and control loops operating inside the payload using fine mechanisms. According to our preliminary study, this mission is feasible within an 8 to 9 years development plan using existing or slightly
improved space components, but its cost requires international cooperation. Pegase could be a valuable Darwin/TPF-I
pathfinder, with a less demanding, but still ambitious, technological challenge and a high associated scientific return.
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