Artist's rendering of the Lunar IceCube spacecraft | |
| Mission type | Lunar orbiter |
|---|---|
| Operator | Morehead State University / NASA |
| COSPAR ID | 2022-156C |
| Mission duration | 4 months and 25 days (in progress) |
| Spacecraft properties | |
| Spacecraft | Lunar IceCube |
| Spacecraft type | CubeSat |
| Bus | 6U CubeSat |
| Manufacturer | Morehead State University |
| Launch mass | 14 kg (31 lb) |
| Dimensions | 10 cm x 20 cm x 30 cm |
| Power | 2 deployable solar panels |
| Start of mission | |
| Launch date | 16 November 2022, 06:47:44 UTC[1] |
| Rocket | SLS Block 1 / Artemis 1 |
| Launch site | KSC, LC-39B |
| Contractor | NASA |
| Orbital parameters | |
| Reference system | Lunar orbit |
| Regime | Polar orbit |
| Periselene altitude | 100 km (62 mi) |
| Inclination | 90° |
| Moon orbiter | |
| Transponders | |
| Band | X-band |
| Instruments | |
| Broadband InfraRed Compact High Resolution Exploration Spectrometer (BIRCHES) | |
Lunar IceCube is a NASA nanosatellite orbiter mission to prospect, locate, and estimate amount and composition of water ice deposits on the Moon for future exploitation by robots or humans.[2] It was launched as a secondary payload mission on Artemis 1 (formerly known as Exploration Mission 1), the first flight of the Space Launch System (SLS), on 16 November 2022.[1][3]
The lunar mission was designed by Morehead State University and its partners, the Busek Company, NASA Goddard Space Flight Center (GSFC), and The Catholic University of America (CUA).[4] It was selected in April 2015 by NASA's NextSTEP program (Next Space Technologies for Exploration Partnerships) and awarded a contract worth up to US$7.9 million for further development.[5][2]
The Lunar IceCube spacecraft will have a 6U CubeSat format, and a mass of about 14 kg (31 lb). It is one of ten CubeSats planned to be carried on board the maiden flight of the SLS, Artemis 1, as secondary payloads in cis-lunar space, in 2022.[3] It will be deployed during lunar trajectory and will use an innovative electric RF ion engine to achieve lunar capture and the science orbit to allow the team to make systematic measurements of lunar water features from an orbit about 100 km (62 mi) above the lunar surface.[2] The principal investigator is Ben Malphrus, Director of the Space Science Center at Morehead State University.[4]
NASA's Lunar Prospector, Clementine, Lunar Crater Observation and Sensing Satellite (LCROSS), the Lunar Reconnaissance Orbiter (LRO) and India's Chandrayaan-1 lunar orbiters and other missions, confirmed both water (H2O) and hydroxyl (—OH−) deposits at high latitudes on the lunar surface, indicating the presence of trace amounts of adsorbed or bound water are present, but their instruments weren't optimized for fully or systematically characterizing the elements in the infrared wavelength bands ideal for detecting water.[4] These missions suggest that there might be enough ice water at polar regions to be used by future landed missions, but the distribution is difficult to reconcile with thermal maps.
Lunar prospecting missions are intended to pave the way toward incorporating use of space resources into mission architectures. NASA's planning for eventual human missions to Mars depends on tapping the local natural resources to make oxygen and propellant for launching the return ship back to Earth, and a lunar precursor mission is a convenient location to test such in situ resource utilization (ISRU) technology.[6]
The science goals are to investigate the distribution of water and other volatiles, as a function of time of day, latitude, and lunar soil composition.[5][2]
Lunar IceCube will include a version of the Broadband InfraRed Compact High Resolution Exploration Spectrometer (BIRCHES) instrument, developed by NASA's Goddard Space Flight Center (GSFC).[4] BIRCHES is a compact version of the volatile-seeking spectrometer instrument onboard the New Horizons Pluto flyby mission.[2]
The tiny CubeSat spacecraft will make use of a miniature electric RF ion engine system based on Busek's 3 centimeter RF ion thruster, also known as BIT-3.[2][7] It utilizes a solid iodine propellant and an inductively-coupled plasma system that produces 1.1 mN thrust and 2800 seconds specific impulse from approximately 50 watts total input power.[7] It will also use this engine for capture into lunar orbit, and orbit adjustments.[2] It is estimated the spacecraft will take about 3 months to reach the Moon.[4]
The flight software is being developed in SPARK/Ada by the Vermont Technical College Cubesat Laboratory.[8] SPARK/Ada has the lowest error rate of any computer language, important for the reliability and success of this complicated spacecraft. It is used in commercial and military aircraft, air traffic control and high speed trains. This is the second spacecraft using SPARK/Ada, the first being the BasicLEO CubeSat [8] also by the Vermont Technical College CubeSat Laboratory, the only fully successful university CubeSat out of 12 on the NASA ELaNa-IV launch on U.S. Air Force Operationally Responsive Space-3 (ORS-3) mission.[9]
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