Session
Session VIII: Instrument/Science Missions
Abstract
Lunar Ice Cube, a science requirements-driven deep space exploration 6U cubesat mission was selected for a NASA HEOMD NextSTEP slot on the EM1 launch. We are developing a compact broadband IR instrument for a high priority science application: understanding volatile origin, distribution, and ongoing processes in the inner solar system. JPL's Lunar Flashlight, and Arizona State University's LunaH-Map, both also EM1 lunar orbiters, will provide complimentary observations to be used in understanding volatile dynamics.
The Lunar Ice Cube mission science focus, led by the JPL science PI, is on enabling broadband spectral determination of composition and distribution of volatiles in regoliths of the Moon and analogous bodies as a function of time of day, latitude, regolith age and composition and thus enabling understanding of current dynamics of volatile sources, sinks, and processes, with implications for evolutionary origin of volatiles.
Lunar Ice Cube utilizes a versatile GSFC-developed payload: BIRCHES, Broadband InfraRed Compact, High-resolution Exploration Spectrometer, a miniaturized version of OVIRS on OSIRIS-REx. BIRCHES is a compact (1.5U, 2 kg, 7W including cryocooler) point spectrometer with a compact cryo-cooled HgCdTe focal plane array for broadband (1 to 4 micron) measurements, achieving sufficient SNR (>400) and spectral resolution (10 nm) through the use of a Linear Variable Filter to characterize and distinguish important volatiles (water, H2S, NH3, CO2, CH4, OH, organics) and mineral bands. We are also developing compact instrument electronics which can be easily reconfigured to support the instrument in 'imager' mode, once the communication downlink band-width becomes available, and the H1RG family of focal plane arrays.
Thermal design is critical for the instrument. The compact and efficient Ricor cryocooler is designed to maintain the detector temperature below 120K. In order to maintain the optical system below 220K, a special radiator is dedicated to optics alone, in addition to a smaller radiator to maintain a nominal environment for spacecraft electronics.
The Lunar Ice Cube team is led by Morehead State University, who will provide build, integrate and test the spacecraft, provide missions operations and ground communication. Propulsion is provided by the Busek Iodine ion propulsion (BIT-3) engine. Attitude Control will be provided by the Blue Canyon Technology XB1, which also includes a C&DH 'bus'. C&DH will also be supported, redundantly, by the Proton 200k Lite and Honeywell DM microprocessor. Onboard communication will be provided by the Xband JPL Iris Radio and dual patch antennas. Ground communication will be provided by the DSN Xband network, particularly the Morehead State University 21-meter substation. Flight Dynamics support, including trajectory design, is provided by GSFC.
Use of a micropropulsion system in a low energy trajectory will allow the spacecraft to achieve the science orbit within a year. The high inclination, equatorial periapsis orbit will allow coverage of overlapping swaths, with a 10 km along-track and cross-track foot-print, once every lunar cycle at up to six different times of day (from dawn to dusk) as the mission progresses during its nominal six month science mapping period.
Lunar Ice Cube: BIRCHES Payload and the Search for Volatiles with a First Generation Deep Space CubeSat
Lunar Ice Cube, a science requirements-driven deep space exploration 6U cubesat mission was selected for a NASA HEOMD NextSTEP slot on the EM1 launch. We are developing a compact broadband IR instrument for a high priority science application: understanding volatile origin, distribution, and ongoing processes in the inner solar system. JPL's Lunar Flashlight, and Arizona State University's LunaH-Map, both also EM1 lunar orbiters, will provide complimentary observations to be used in understanding volatile dynamics.
The Lunar Ice Cube mission science focus, led by the JPL science PI, is on enabling broadband spectral determination of composition and distribution of volatiles in regoliths of the Moon and analogous bodies as a function of time of day, latitude, regolith age and composition and thus enabling understanding of current dynamics of volatile sources, sinks, and processes, with implications for evolutionary origin of volatiles.
Lunar Ice Cube utilizes a versatile GSFC-developed payload: BIRCHES, Broadband InfraRed Compact, High-resolution Exploration Spectrometer, a miniaturized version of OVIRS on OSIRIS-REx. BIRCHES is a compact (1.5U, 2 kg, 7W including cryocooler) point spectrometer with a compact cryo-cooled HgCdTe focal plane array for broadband (1 to 4 micron) measurements, achieving sufficient SNR (>400) and spectral resolution (10 nm) through the use of a Linear Variable Filter to characterize and distinguish important volatiles (water, H2S, NH3, CO2, CH4, OH, organics) and mineral bands. We are also developing compact instrument electronics which can be easily reconfigured to support the instrument in 'imager' mode, once the communication downlink band-width becomes available, and the H1RG family of focal plane arrays.
Thermal design is critical for the instrument. The compact and efficient Ricor cryocooler is designed to maintain the detector temperature below 120K. In order to maintain the optical system below 220K, a special radiator is dedicated to optics alone, in addition to a smaller radiator to maintain a nominal environment for spacecraft electronics.
The Lunar Ice Cube team is led by Morehead State University, who will provide build, integrate and test the spacecraft, provide missions operations and ground communication. Propulsion is provided by the Busek Iodine ion propulsion (BIT-3) engine. Attitude Control will be provided by the Blue Canyon Technology XB1, which also includes a C&DH 'bus'. C&DH will also be supported, redundantly, by the Proton 200k Lite and Honeywell DM microprocessor. Onboard communication will be provided by the Xband JPL Iris Radio and dual patch antennas. Ground communication will be provided by the DSN Xband network, particularly the Morehead State University 21-meter substation. Flight Dynamics support, including trajectory design, is provided by GSFC.
Use of a micropropulsion system in a low energy trajectory will allow the spacecraft to achieve the science orbit within a year. The high inclination, equatorial periapsis orbit will allow coverage of overlapping swaths, with a 10 km along-track and cross-track foot-print, once every lunar cycle at up to six different times of day (from dawn to dusk) as the mission progresses during its nominal six month science mapping period.
