Memory and Storage

Memory devices and storage architectures used by flown planetary and orbital robotics programs, and the in-flight upset and wear data published for them.

The two long-duration flight records here point in opposite directions. ISS multiplexer DRAM upsets are frequent, individually harmless and corrected inside the refresh cycle [1]. Curiosity’s NAND flash degraded in a way that took a whole computer string out of service [2]. Soft error rate is a design parameter; wear-out is an operations problem. See Notable results below.

Memory and storage devices selected and flown

Part	Manufacturer	Used by	Source
TMS44400 1Mx4 DRAM	Texas Instruments	ISS multiplexers	[1]
MT29F4G08AAA NAND flash	Micron	curiosity	[2][10]
128 Mbyte SDRAM, 8 Gbyte NAND flash	Not named	curiosity (MAHLI), perseverance (Mastcam-Z)	[3][4]
Start-up PROM with MRAM and SDRAM	Cobham Aeroflex	perseverance (SuperCam Body Unit)	[5]
32 kbyte PROM, 128 kbyte MRAM, SDRAM	Not named	perseverance (SuperCam Mast Unit)	[6]
6 Mbyte data bank, two EEPROM banks	Not named	curiosity (ChemCam DPU)	[7]

Ratings and qualification results

TMS44400 1Mx4 DRAM, Texas Instruments: commercial DRAM screened for flight, in the ISS command and data handling multiplexers, the bus that hosts canadarm2 and dextre [1]. Ratings: Eight devices per multiplexer demultiplexer for 33,554,432 bits. A Hamming single-error-correction double-error-detection code is embedded in the DRAM refresh and scrub cycle, which starts every 8 microseconds and takes 8.2 seconds to sweep memory, holding the maximum residence time of a soft error in a data word below 10 microseconds [1]. Qualification: Measured in flight over 2005 to 2017 and set against the Peterson figure-of-merit prediction for the same part. At 10 g/cm2 median shielding, external units, the all-region in-flight rate is 8.5e-8 SEU per bit-day against a figure-of-merit prediction of 2.5e-7, an overestimate by a factor of 2.9 [1]. Of the counts logged from February 2010 through 2017, 39 percent plus or minus 4 fall inside the South Atlantic Anomaly for the twelve external units against 13 percent plus or minus 9 for the eight internal units at about 40 g/cm2, and of the counts outside the anomaly 68 percent plus or minus 4 fall poleward of 40 degrees latitude, a band holding 39 percent of flight time [1].
MT29F4G08AAA NAND flash, Micron, in the Rover Compute Element non-volatile memory card. Non-volatile mass storage in the flight computer string, named to part number only in the thermal fatigue investigation [10]. Ratings: Each RCE carries 512 Mbytes of RAM under VxWorks alongside its flash [2]. Qualification: Wear-out in flight. A failing region of RCE-A NAND flash forced a swap to RCE-B on sol 201. The RCE-B data product partition then failed to mount on sol 2173, forcing a return to RCE-A on sol 2188 until RCE-B was reformatted on sol 2342. RCE-A carried 1,158.793 m of odometry and RCE-B 20,159.565 m, so 94.37 percent of the mission has run on the backup string [2].
128 Mbyte SDRAM, 8 Gbyte NAND flash, vendor not named [3][4]. Camera-local image buffer in the Digital Electronics Assembly. Ratings: The flash is organized as a large image buffer so images can be acquired at maximum camera data rate without consuming rover memory; the SDRAM holds the working image pipeline [3][4]. Qualification: Flown on two rovers since August 2012 and February 2021. The architectural point is that the buffer decouples camera frame rate from the rover computer, which is what allows the onboard pipeline to run at full camera head input rate [3][4].
Start-up PROM with MRAM and SDRAM, Cobham Aeroflex [5]. A start-up read-only memory module, three 2 Mbyte MRAM devices and one 2.5 Gbit SDRAM in the SuperCam Body Unit command and data handling. Ratings: MRAM holds non-volatile program and parameter storage; SDRAM holds volatile program space and data buffers [5]. Qualification: The SUROM can interface with the rover compute element and accept a limited command set that rewrites corrupt program memory on Mars, so a program memory corruption is recoverable in flight rather than terminal [5].
32 kbyte PROM, 128 kbyte MRAM, SDRAM, vendor not named, inside the Mast Unit data processing unit [6]. One-time-programmable boot PROM, non-volatile application store and a 32 M x 16 bit image buffer. Ratings: PROM holds the boot flight software, MRAM the application flight software with transfer function equations and configuration tables, SDRAM the Remote Micro-Imager images and acoustic recordings [6]. The Mast Unit can store three different application codes for redundancy [6]. Qualification: The application software is reprogrammable on Mars by patch command while the boot software is not. SDRAM in this design is explicitly SEU-sensitive and was accepted with a calculated non-destructive failure rate of about one event for the nominal mission [6].
6 Mbyte data bank, two EEPROM banks, vendor not named [7]. Volatile data store with dual non-volatile program banks. Ratings: One EEPROM bank has its write line tied off to the inactive state in hardware so it cannot be written in flight; the other is reprogrammable from the ground [7]. Qualification: Flown since August 2012. The hardware write-lock is the design answer to the corruption risk that SuperCam later answered in software with a SUROM recovery path [7][5].

Upset rates measured in flight, and flash wear-out

The ISS multiplexer DRAM has a twelve-year in-flight upset record set against the prediction made for the same part. ISS multiplexer DRAM upsets are corrected by a Hamming single-error-correction double-error-detection code embedded in the memory refresh and scrub cycle, and every corrected upset is logged with the ISS location, which is what makes the measurement possible [1]. At 10 g/cm2 median shielding the TMS44400 in-flight rate is 8.5e-8 SEU per bit-day against a Peterson figure-of-merit prediction of 2.5e-7, so the prediction is high by a factor of 2.9, inside the factor of 2 to 5 overestimate the method is expected to give. Shielding does not act in one direction. Between February 2010 and 2017 the internal units at about 40 g/cm2 logged fewer upsets inside the South Atlantic Anomaly than the external units at about 10 g/cm2, 13 percent of their counts against 39 percent, and more outside it, a mean of 6030 counts against 5367, which the authors attribute to secondary particle showers raised by galactic cosmic rays in the heavier structure [1]. Added shielding therefore trades trapped-proton upsets for secondary-particle upsets rather than removing upsets.

Flash wear-out, not radiation, took a Curiosity computer string out of service. A failing region of Curiosity RCE-A NAND flash forced a swap to the RCE-B computer string on sol 201; the RCE-B data product partition then failed to mount on sol 2173, forcing a return to RCE-A on sol 2188 until RCE-B was reformatted on sol 2342 [2]. RCE-A has carried 1,158.793 m of odometry and RCE-B 20,159.565 m, so 94.37 percent of the mission has run on what was launched as the backup string.

Thermal fatigue does not explain the first of those failures. Counted against the accelerated cycling test run on the same board design for Mars 2020, the RCE-A flash had accumulated under a third of the cycles at which that test cracked solder joints when it failed to mount on sol 200, while RCE-B, which carried the mission afterward, had accumulated three times as many [10]. The build record runs the same way round: the NVMCAM-B board was reworked several times while NVMCAM-A had clean paperwork. No joint from either flight unit has been inspected, so loss of electrical connectivity is a leading theory rather than a diagnosis, and the sol 2172 root cause was lost when the diagnostic data was compacted.

Ground prediction against measured flight rate

Two DRAM part types have a figure-of-merit prediction made from heavy-ion ground cross sections and a flight rate measured afterwards on the same part [1]:

Part and orbit	Ground prediction	Flight measurement	Ratio
TMS44400 DRAM, ISS	2.5e-7 upsets/bit day	8.5e-8 upsets/bit day	2.9x high
SMJ44100 DRAM, SOHO at L1	1.6e-6 upsets/bit day	5.9e-7 upsets/bit day	2.7x high

TMS44400 DRAM, ISS, Texas Instruments. All-region in-flight rate at 10 g/cm2 median shielding over 2010 to 2017, against a Petersen figure-of-merit prediction built from heavy-ion ground cross sections [1].
SMJ44100 DRAM, SOHO, Texas Instruments. Same method, at Earth-Sun L1 behind 1 g/cm2 of shielding [1].

Both predictions are conservative and by nearly the same factor, which is the behavior a Petersen figure of merit is expected to show. Scaling the measured ISS rate to L1 conditions gives 4.4e-7 upsets/bit day against the 5.9e-7 measured on SOHO, agreeing within a factor of 1.3 [1]: a flight rate carried to another orbit landed closer than either ground prediction did in its own. Both are one part type, so nothing here transfers to a modern deep submicron memory [1]. The two whole-article cases from the same campaign, the ISS crew laptops, are on Processors and spread much wider.

What a write-lock buys

Three of the six rows are the same problem solved three ways. ChemCam ties one EEPROM write line off in hardware [7]. SuperCam’s Body Unit keeps a start-up PROM that can be commanded from the rover to repair corrupt program memory [5]. The SuperCam Mast Unit keeps three application codes in MRAM and makes only the boot image immutable [6]. All three accept that program memory can be corrupted in flight and differ only in what remains trustworthy afterwards.

Non-volatile memory characterized against radiation, not yet flown on a planetary robot

Part	Manufacturer	Facility and date	Source
AS216MA1G2B-ASC	Avalanche Technology	Lawrence Berkeley 88-Inch Cyclotron, May 2019	[8]
ASV016204	Avalanche Technology	Naval Research Laboratory laser, January 2020	[8]
Cypress FRAM	Cypress	Massachusetts General Hospital, June 2019	[8]
MT29F4T08CTHBBM5	Micron	Goddard Space Flight Center, April 2019	[8]
MT29F1T08 3D NAND flash	Micron	Lawrence Berkeley cyclotron, November 2019	[8]
H25QFT8F4A9R-BDF	SK Hynix	Lawrence Berkeley 88-Inch Cyclotron, November 2019	[8]
MSP430, ferroelectric memory	Texas Instruments	In-house dose testing, 2021	[9]

Ratings and campaign results

AS216MA1G2B-ASC, Avalanche Technology [8]. 40 nm CMOS MRAM, tested at the Lawrence Berkeley National Laboratory 88-Inch Cyclotron in May 2019 and under the Naval Research Laboratory laser in June 2019. Ratings: Magnetoresistive cell, so the stored state is not a trapped charge and does not wear with write cycles. Qualification: Single event latch-up observed with a threshold linear energy transfer between 21.1 and 58.8 MeV-cm2/mg; latch-up also triggered by pulsed laser at about 40 pJ [8].
ASV016204, Avalanche Technology [8]. 40 nm CMOS MRAM, tested under the Naval Research Laboratory laser in January 2020 and in Goddard Space Flight Center gamma in February 2020. Ratings: Same cell technology, later lot. Qualification: No single event effects at 80 C under pulsed laser at 21.6 pJ, and no parametric degradation at 1 Mrad(Si) gamma [8].
Cypress FRAM, Cypress, as boot and user memory on the Vorago RH-OBC-1. Ferroelectric non-volatile memory, tested at the Francis Burr Proton Therapy Center at Massachusetts General Hospital. Ratings: Non-volatile without an erase cycle, so no flash wear-out mechanism. Qualification: Both devices took single event functional interrupts under 200 MeV protons [8]. The board had no way to gate their power, so a boot FRAM SEFI left the microcontroller unable to reload boot code without an external power cycle. The vendor mitigation is to power the boot device down when it is not in use.
MT29F4T08CTHBBM5, Micron [8]. 3D NAND flash. Ratings: Multi-level cell mode available. Qualification: Erase circuitry failed at 39 krad(Si) under gamma, with the error rate rising faster in multi-level cell mode than in single-level [8].
MT29F1T08 3D NAND flash, Micron [8]. 3D NAND flash tested under heavy ions at the Lawrence Berkeley National Laboratory 88-Inch Cyclotron in November 2019, on a single part, with the compendium’s reported threshold defined as the highest linear energy transfer at which nothing was seen at an effective fluence of 1e7 particles/cm2. Ratings: a single sample, so the result bounds this part and not the part type. Qualification: no single event latch-up to 85 MeV-cm2/mg at 78 C, the highest linear energy transfer the run reached, with single event functional interrupts observed [8].
H25QFT8F4A9R-BDF, SK Hynix [8]. 3D NAND flash. Ratings: Single-level and triple-level cell modes. Qualification: Upset threshold linear energy transfer below 1.16 MeV-cm2/mg in single-level mode and below 3.08 in triple-level; functional interrupt threshold between 1.54 and 7.27; two parts suffered destructive events at 58.8 MeV-cm2/mg at 80 C [8].
MSP430, ferroelectric memory, Texas Instruments. Microcontroller with a non-volatile ferroelectric program store. Ratings: Program memory immune to the radiation effects that afflict flash program store. Qualification: Carried across the MoonRanger power, thermal and motor control boards on CubeSat flight heritage, with in-house dose testing levied on the boards.

MRAM and FRAM remove the wear-out mechanism that took a Curiosity computer string out of service, and both are non-volatile without an erase cycle. Neither removes single event effects: the 40 nm MRAM latched up under heavy ions, and the FRAM devices on a radiation-hardened board took functional interrupts the board could not recover from [8].

Memory devices in the radiation compendia

Commercial memory characterized at a named beam for the NASA Electronic Parts and Packaging program, none of it flown on a planetary robot. Densities span two orders of magnitude and the upset thresholds do not [11][12].

Part	Manufacturer	Facility	Source
MT29F32G08ABAAA, MT29F64G08CBAAA, MT29F128G08EFAAA	Micron	Texas A and M cyclotron	[11]
MT29F8G08U0M	Micron	Texas A and M cyclotron	[12]
MT46V64M8 SDRAM	Micron	Brookhaven, Indiana	[12]
EDS5104ABTA-75 SDRAM	Elpida	Texas A and M cyclotron	[12]
EDS5108ABTA SDRAM	Elpida	Brookhaven	[11]
K9F8G08U0M, K9G8G08U0A	Samsung	Texas A and M, RADEF	[12]
S29GL512 NOR flash	Spansion	Brookhaven, UC Davis	[12]
22FDX SRAM test vehicle	GlobalFoundries	Goddard gamma irradiator	[8]

Ratings and campaign results

MT29F32G08ABAAA, MT29F64G08CBAAA, MT29F128G08EFAAA, Micron. Commercial planar NAND flash at 32, 64 and 128 Gbit [11]. Ratings: single-level cell array, no error correction inside the device. Qualification: upset threshold below 0.1 MeV-cm2/mg on all three, with saturated cross sections of about 1e-10 cm2 per bit on the 32 Gbit part and about 1e-9 on the other two [11]. A threshold that low is below the lightest ion the beam can deliver, so the number bounds the part from above and does not locate it.
MT29F8G08U0M, Micron [12]. Commercial 8 Gbit single-level cell NAND flash. Ratings: planar array with no on-die error correction. Qualification: destructive high-current spikes observed under heavy ion in PROGRAM mode [12]. The event is mode dependent, so a screen run only in READ passes a part that fails when it is written.
MT46V64M8 SDRAM, Micron. Commercial 64 Mbit DDR SDRAM [12]. Ratings: volatile working memory. Qualification: upset threshold below 8 MeV-cm2/mg under heavy ion at Brookhaven, and a proton upset threshold below 50 MeV at the Indiana University Cyclotron Facility with no latchup at 50 MeV [12].
EDS5104ABTA-75 SDRAM, Elpida. Commercial 512 Mbit SDRAM [12]. Ratings: volatile, no internal error correction. Qualification: upset threshold above 2.7 MeV-cm2/mg with a saturated cross section near 2e-1 per device, a recoverable mode-register functional interrupt above 3.8 MeV-cm2/mg, and above 5.4 MeV-cm2/mg a mode returning over a thousand errors in a row that clears only on a rewrite or a power cycle [12]. The three thresholds sit within a factor of two of each other, so a beam that upsets the part is close to the beam that takes it out of service.
EDS5108ABTA SDRAM, Elpida. Commercial SDRAM of the same family. Ratings: volatile. Qualification: upset and functional-interrupt thresholds both below 2 MeV-cm2/mg at Brookhaven, saturated cross sections about 2e-9 cm2 per bit and 2e-9 cm2 per device [11].
K9F8G08U0M, K9G8G08U0A, Samsung. Commercial 8 Gbit NAND flash, single-level and multi-level cell [12]. Ratings: the multi-level part stores two bits per cell. Qualification: destructive high-current spikes on the single-level part in both READ and PROGRAM modes; on the multi-level part, latchup below 35 MeV-cm2/mg at 25 C and an upset threshold below 4 MeV-cm2/mg at RADEF [12].
S29GL512 NOR flash, Spansion. Commercial 512 Mbit NOR flash [12]. Ratings: execute-in-place program store. Qualification: upset threshold below 4 MeV-cm2/mg under heavy ion at Brookhaven and below 20 MeV under protons at the UC Davis Crocker Nuclear Laboratory, with no latchup in either run [12].
22FDX SRAM test vehicle, GlobalFoundries [8]. Fully depleted silicon-on-insulator SRAM test chip, not a product. Ratings: a process evaluation vehicle rather than a memory part. Qualification: over half the bits were stuck between 300 and 500 krad(Si) of gamma, and the devices remained functional at that level [8].

Every threshold above is a heavy-ion or proton screen taken on two or three parts. None of them carries an upset rate for an orbit, and the two destructive results, the Micron and Samsung single-level parts, are the only entries that bound a part rather than a beam.

SDRAM stuck bits, and one memory with a flight rate

Part	Manufacturer	Facility	Source
IS42S86400B SDRAM	ISSI	JPL cobalt-60	[13]
IS43DR81280 DDR2 SDRAM	ISSI	JPL cobalt-60	[13]
HM-6508 1K CMOS RAM	Harris	Low polar Earth orbit	[14]
HM65656 256K SRAM	Matra	Michigan State NSCL	[15]
71256 256K SRAM	IDT	Michigan State NSCL	[15]

Ratings and campaign results

IS42S86400B SDRAM, ISSI. Commercial SDRAM under gamma at 15 to 20 rad(Si)/s [13]. Ratings: 3.6 V at room temperature, read back at a 32 ms refresh. Qualification: stuck bits appear uniformly across the die with no banding or clustering and no more than one per 8 bit transfer, each analyzed cell covering 2048 bytes [13]. Refreshing the part during irradiation rather than holding it under static bias raised the stuck bit count by up to a factor of 1e5 [13]. Whether the part is being exercised during the exposure changes the answer by five orders of magnitude, which is a test condition and not a part property.
IS43DR81280 DDR2 SDRAM, ISSI. Ratings: 1.9 V, tested both static and with refresh on [13]. Qualification: no device failures to 400 krad(Si) and no stuck bits at all at a 1 s readout, at which point testing stopped [13]. That is where the campaign ended, not where the part failed.
HM-6508 1K CMOS RAM, Harris [14]. Ratings: 384 chips flown in low polar Earth orbit near solar minimum, checked by periodic memory checksum and a monthly full dump against the load file [14]. Qualification: 7.6e-2 upsets per chip-year measured over 731 days from January 1983, or 9.4e-2 counting each bit error rather than each event, against an upper limit of 1.3e-3 latchups per chip-year from two years with no latchup. Of 58 upset events, 47 were single bit and 11 produced 72 bit errors between them, and the affected bits lie adjacent on the die; two independent errors inside one 90 minute verification interval would be expected about once in 13 years, so 19 percent of events are single-track multiple-bit upsets [14]. A prediction built from 88-inch cyclotron data at a critical charge of 0.29 pC crosses the measured band at a few g/cm2 of aluminum, which the authors describe as about the average spacecraft shielding.
HM65656 256K SRAM, Matra [15]. Ratings: delidded for the test. Qualification: upset cross section 1.35e-3 cm2 under 9574 MeV krypton at 7.1 MeV-cm2/mg [15].
71256 256K SRAM, IDT, in a plastic package [15]. Ratings: tested against a delidded part of the same type under a degraded krypton beam. Qualification: the plastic part returned an apparent upset cross section 100 times lower, because the ions ranged out in the package before reaching the sensitive volume [15]. The result is an artifact of the package, and a screen run this way passes a part that has not been irradiated.

The HM-6508 is the only memory in this database with an upset rate measured in orbit rather than derived from a beam, and its multiple-bit fraction, 19 percent of events, is the quantity a single-bit correcting code does not cover [14].

References

Koontz, S. L., Suggs, R. M., Alred, J. W., Worthy, E. S., Boeder, P., Steagall, C. A., Hartman, W. A., Gingras, B. D. and Schmidl, W. D. (2018). The International Space Station Space Radiation Environment: Avionics Systems Performance in Low-Earth Orbit Single Event Effects (SEE) Environments . International Conference on Environmental Systems, ICES-2018-69. Source

BibTeX

@inproceedings{koontz2018international,
  title = {The International Space Station Space Radiation Environment: Avionics Systems Performance in Low-Earth Orbit Single Event Effects (SEE) Environments},
  author = {Koontz, Steven L. and Suggs, Robert M. and Alred, John W. and Worthy, Erica S. and Boeder, Paul and Steagall, Courtney A. and Hartman, William A. and Gingras, Benjamin D. and Schmidl, William D.},
  booktitle = {International Conference on Environmental Systems},
  number = {ICES-2018-69},
  address = {Albuquerque, New Mexico},
  year = {2018},
  url = {https://ttu-ir.tdl.org/items/7fb5d403-ad77-4f6b-9cff-c70af5c04802}
}

Rankin, A., Maimone, M., Biesiadecki, J., Patel, N., Levine, D. and Toupet, O. (2021). Mars Curiosity Rover Mobility Trends During the First Seven Years . Journal of Field Robotics, 5. Source

BibTeX

@article{rankin2021mars,
  title = {Mars Curiosity Rover Mobility Trends During the First Seven Years},
  author = {Rankin, Arturo and Maimone, Mark and Biesiadecki, Jeffrey and Patel, Nikunj and Levine, Dan and Toupet, Olivier},
  journal = {Journal of Field Robotics},
  volume = {38},
  number = {5},
  pages = {759--800},
  year = {2021},
  doi = {10.1002/rob.22011},
  abstract = {Abstract NASA's Mars Science Laboratory (MSL) Curiosity rover landed on Mars on August 6, 2012. In the 7 years between landing and August 6, 2019 (sol 2488), Curiosity has driven 21,318.5 m over a variety of terrain types and slopes, employing multiple drive modes with varying amounts of onboard autonomy. Curiosity's drive distances each sol have ranged from its shortest drive of 2.6 cm to its longest drive of 142.5 m, with an average drive distance of 28.9 m. Real‐time human intervention is not possible during Curiosity's drives due to the latency in uplinking commands and downlinking telemetry. Instead, the operations team relies on Curiosity's fault protection, autonomous navigation, and visual odometry software to keep the rover safe during drives. During its first 7 years on Mars, Curiosity has attempted 738 drives. While 622 drives ran to completion, 116 drives were prevented or stopped early by Curiosity's fault protection software. The primary risks to mobility success have been wheel damage, wheel entrapment, progressive wheel sinkage, and the potential for hardware or cable failures that result in an inability to command one or more steer or drive actuators. In this paper, we describe Curiosity's mobility subsystem, mobility trends over the first 21.3 km of the mission, operational aspects of mobility fault protection, risks to continued mobility success, and risk mitigation strategies.}
}

Edgett, K. S., Yingst, R. A., Ravine, M. A., Caplinger, M. A., Maki, J. N., Ghaemi, F. T., Schaffner, J. A., Bell, I. J. F., Edwards, L. J., Herkenhoff, K. E., Heydari, E., Kah, L. C., Lemmon, M. T., Minitti, M. E., Olson, T. S., Parker, T. J., Rowland, S. K., Schieber, J., Sullivan, R. J., Sumner, D. Y., Thomas, P. C., Jensen, E. H., Simmonds, J. J., Sengstacken, A. J., Willson, R. G. and Goetz, W. (2012). Curiosity's Mars Hand Lens Imager (MAHLI) Investigation . Space Science Reviews. Source

BibTeX

@article{edgett2012curiosity,
  title = {Curiosity's Mars Hand Lens Imager (MAHLI) Investigation},
  author = {Edgett, Kenneth S. and Yingst, R. Aileen and Ravine, Michael A. and Caplinger, Michael A. and Maki, Justin N. and Ghaemi, F. Tony and Schaffner, Jacob A. and Bell, III, James F. and Edwards, Laurence J. and Herkenhoff, Kenneth E. and Heydari, Ezat and Kah, Linda C. and Lemmon, Mark T. and Minitti, Michelle E. and Olson, Timothy S. and Parker, Timothy J. and Rowland, Scott K. and Schieber, Juergen and Sullivan, Robert J. and Sumner, Dawn Y. and Thomas, Peter C. and Jensen, Elsa H. and Simmonds, John J. and Sengstacken, Aaron J. and Willson, Reg G. and Goetz, Walter},
  journal = {Space Science Reviews},
  volume = {170},
  pages = {259--317},
  year = {2012},
  doi = {10.1007/s11214-012-9910-4},
  abstract = {The Mars Science Laboratory (MSL) Mars Hand Lens Imager (MAHLI) investigation will use a 2-megapixel color camera with a focusable macro lens aboard the rover, Curiosity, to investigate the stratigraphy and grain-scale texture, structure, mineralogy, and morphology of geologic materials in northwestern Gale crater. Of particular interest is the stratigraphic record of a ∼5 km thick layered rock sequence exposed on the slopes of Aeolis Mons (also known as Mount Sharp). The instrument consists of three parts, a camera head mounted on the turret at the end of a robotic arm, an electronics and data storage assembly located inside the rover body, and a calibration target mounted on the robotic arm shoulder azimuth actuator housing. MAHLI can acquire in-focus images at working distances from ∼2.1 cm to infinity. At the minimum working distance, image pixel scale is ∼14 μm per pixel and very coarse silt grains can be resolved. At the working distance of the Mars Exploration Rover Microscopic Imager cameras aboard Spirit and Opportunity, MAHLI’s resolution is comparable at ∼30 μm per pixel. Onboard capabilities include autofocus, auto-exposure, sub-framing, video imaging, Bayer pattern color interpolation, lossy and lossless compression, focus merging of up to 8 focus stack images, white light and longwave ultraviolet (365 nm) illumination of nearby subjects, and 8 gigabytes of non-volatile memory data storage.}
}

Bell, I. J., Maki, J. N., Mehall, G. L., Ravine, M. A., Caplinger, M. A., Bailey, Z., Brylow, S., Schaffner, J. A., Kinch, K. M., Madsen, M., Winhold, A. G., Hayes, A. G., Corlies, P., Tate, C., Barrington, M., Cisneros, E., Jensen, E., Paris, K., Crawford, K., Rojas, C., Mehall, L., Joseph, J., Proton, J., Cluff, N., Deen, R. G., Betts, B., Cloutis, E., Coates, A. J., Colaprete, A., Edgett, K. S., Ehlmann, B. L., Fagents, S. A., Grotzinger, J. P., Hardgrove, C., Herkenhoff, K., Horgan, B., Jaumann, R., Johnson, J. R., Lemmon, M., Paar, G., Caballo-Perucha, M., Gupta, S., Traxler, C., Preusker, F., Rice, M. S., Robinson, M. S., Schmitz, N., Sullivan, R. and Wolff, M. (2021). The Mars 2020 Perseverance Rover Mast Camera Zoom (Mastcam-Z) Multispectral, Stereoscopic Imaging Investigation . Space Science Reviews, 24. Source

BibTeX

@article{bell2021mars,
  title = {The Mars 2020 Perseverance Rover Mast Camera Zoom (Mastcam-Z) Multispectral, Stereoscopic Imaging Investigation},
  author = {Bell, III, J.F. and Maki, Justin N. and Mehall, Greg L. and Ravine, Michael A. and Caplinger, Michael A. and Bailey, Z.J. and Brylow, S. and Schaffner, Jacob A. and Kinch, Kjartan M. and Madsen, M.B. and Winhold, Andrew G. and Hayes, Alexander G. and Corlies, Paul and Tate, C. and Barrington, Megan and Cisneros, Ernest and Jensen, E. and Paris, Kristen and Crawford, Kelsie and Rojas, Corrine and Mehall, Laura and Joseph, Jonathan and Proton, J.B. and Cluff, Nathan and Deen, Robert G. and Betts, B. and Cloutis, E. and Coates, Andrew J. and Colaprete, Anthony and Edgett, Kenneth S. and Ehlmann, Bethany L. and Fagents, Sarah A. and Grotzinger, John P. and Hardgrove, Craig and Herkenhoff, K.E. and Horgan, B. and Jaumann, Ralf and Johnson, Jeffrey R. and Lemmon, M. and Paar, Gerhard and Caballo-Perucha, M. and Gupta, Sanjeev and Traxler, Christoph and Preusker, Frank and Rice, Melissa S. and Robinson, Mark S. and Schmitz, Nicole and Sullivan, R. and Wolff, M.J.},
  journal = {Space Science Reviews},
  volume = {217},
  number = {24},
  pages = {24--24},
  year = {2021},
  doi = {10.1007/s11214-020-00755-x},
  abstract = {Abstract Mastcam-Z is a multispectral, stereoscopic imaging investigation on the Mars 2020 mission’s Perseverance rover. Mastcam-Z consists of a pair of focusable, 4:1 zoomable cameras that provide broadband red/green/blue and narrowband 400-1000 nm color imaging with fields of view from 25.6° × 19.2° (26 mm focal length at 283 μrad/pixel) to 6.2° × 4.6° (110 mm focal length at 67.4 μrad/pixel). The cameras can resolve (≥ 5 pixels) ∼0.7 mm features at 2 m and ∼3.3 cm features at 100 m distance. Mastcam-Z shares significant heritage with the Mastcam instruments on the Mars Science Laboratory Curiosity rover. Each Mastcam-Z camera consists of zoom, focus, and filter wheel mechanisms and a 1648 × 1214 pixel charge-coupled device detector and electronics. The two Mastcam-Z cameras are mounted with a 24.4 cm stereo baseline and 2.3° total toe-in on a camera plate ∼2 m above the surface on the rover’s Remote Sensing Mast, which provides azimuth and elevation actuation. A separate digital electronics assembly inside the rover provides power, data processing and storage, and the interface to the rover computer. Primary and secondary Mastcam-Z calibration targets mounted on the rover top deck enable tactical reflectance calibration. Mastcam-Z multispectral, stereo, and panoramic images will be used to provide detailed morphology, topography, and geologic context along the rover’s traverse; constrain mineralogic, photometric, and physical properties of surface materials; monitor and characterize atmospheric and astronomical phenomena; and document the rover’s sample extraction and caching locations. Mastcam-Z images will also provide key engineering information to support sample selection and other rover driving and tool/instrument operations decisions.}
}

Maurice, S., Wiens, R. C., Bernardi, P., Caïs, P., Robinson, S. H., Nelson, T., Gasnault, O., Reess, J.-M., Deleuze, M., Rull, F., Manrique, J. A., Abbaki, S., Anderson, R. B., André, Y., Angel, S., Arana, G., Battault, T., Beck, P., Benzerara, K., Bernard, S., Berthias, J.-P., Beyssac, O., Bonafous, M., Bousquet, B., Boutillier, M., Cadu, A., Castro, K., Chapron, F., Chide, B., Clark, K., Clavé, E., Clegg, S., Cloutis, E., Collin, C., Cordoba, E. C., Cousin, A., Dameury, J.-C., D'Anna, W., Daydou, Y., Debus, A., Deflores, L., Dehouck, E., Delapp, D., De Los Santos, G., Donny, C., Doressoundiram, A., Dromart, G., Dubois, B., Dufour, A., Dupieux, M., Egan, M., Ervin, J., Fabre, C., Fau, A., Fischer, W., Forni, O., Fouchet, T., Frydenvang, J., Gauffre, S., Gauthier, M., Gharakanian, V., Gilard, O., Gontijo, I., Gonzalez, R., Granena, D., Grotzinger, J., Hassen-Khodja, R., Heim, M., Hello, Y., Hervet, G., Humeau, O., Jacob, X., Jacquinod, S., Johnson, J. R., Kouach, D., Lacombe, G., Lanza, N., Lapauw, L., Laserna, J., Lasue, J., Le Deit, L., Le Mouélic, S., Le Comte, E., Lee, Q.-M., Legett, I. C., Leveille, R., Lewin, E., Leyrat, C., Lopez-Reyes, G., Lorenz, R., Lucero, B., Madariaga, J. M., Madsen, S., Madsen, M., Mangold, N., Manni, F., Mariscal, J.-F., Martinez-Frias, J., Mathieu, K., Mathon, R., McCabe, K. P., McConnochie, T., McLennan, S. M., Mekki, J., Melikechi, N., Meslin, P.-Y., Micheau, Y., Michel, Y., Michel, J. M., Mimoun, D., Misra, A., Montagnac, G., Montaron, C., Montmessin, F., Moros, J., Mousset, V., Morizet, Y., Murdoch, N., Newell, R. T., Newsom, H., Nguyen Tuong, N., Ollila, A. M., Orttner, G., Oudda, L., Pares, L., Parisot, J., Parot, Y., Pérez, R., Pheav, D., Picot, L., Pilleri, P., Pilorget, C., Pinet, P., Pont, G., Poulet, F., Quantin-Nataf, C., Quertier, B., Rambaud, D., Rapin, W., Romano, P., Roucayrol, L., Royer, C., Ruellan, M., Sandoval, B., Sautter, V., Schoppers, M. J., Schröder, S., Seran, H.-C., Sharma, S. K., Sobron, P., Sodki, M., Sournac, A., Sridhar, V., Standarovsky, D., Storms, S., Striebig, N., Tatat, M., Toplis, M., Torre-Fdez, I., Toulemont, N., Velasco, C., Veneranda, M., Venhaus, D., Virmontois, C., Viso, M., Willis, P. and Wong, K. (2021). The SuperCam Instrument Suite on the Mars 2020 Rover: Science Objectives and Mast-Unit Description . Space Science Reviews, 47. Source

BibTeX

@article{maurice2021supercam,
  title = {The SuperCam Instrument Suite on the Mars 2020 Rover: Science Objectives and Mast-Unit Description},
  author = {Maurice, Sylvestre and Wiens, Roger C. and Bernardi, Pernelle and Caïs, Phillippe and Robinson, Scott H. and Nelson, Tony and Gasnault, Olivier and Reess, Jean-Michel and Deleuze, Muriel and Rull, Fernando and Manrique, Jose Antonio and Abbaki, Sadok and Anderson, Ryan B. and André, Yves and Angel, S.M. and Arana, Gorka and Battault, T. and Beck, Pierre and Benzerara, Karim and Bernard, Sylvain and Berthias, J.-P. and Beyssac, Olivier and Bonafous, Marion and Bousquet, Bruno and Boutillier, M. and Cadu, A. and Castro, Kepa and Chapron, Frédéric and Chide, Baptiste and Clark, K. and Clavé, Elise and Clegg, S. and Cloutis, E. and Collin, Claude and Cordoba, Elizabeth C. and Cousin, A. and Dameury, J.-C. and D'Anna, W. and Daydou, Yves and Debus, Andre and Deflores, Lauren and Dehouck, Erwin and Delapp, Dorothea and De Los Santos, Greg and Donny, C. and Doressoundiram, Alain and Dromart, Gilles and Dubois, Bruno and Dufour, A. and Dupieux, M. and Egan, Miles and Ervin, Joan and Fabre, C. and Fau, Amaury and Fischer, Woodward and Forni, Olivier and Fouchet, Thierry and Frydenvang, Jens and Gauffre, S. and Gauthier, M. and Gharakanian, V. and Gilard, Olivier and Gontijo, Ivair and Gonzalez, R. and Granena, D. and Grotzinger, J. and Hassen-Khodja, Rafik and Heim, M. and Hello, Y. and Hervet, G. and Humeau, Olivier and Jacob, Xavier and Jacquinod, Sophie and Johnson, Jeffrey R. and Kouach, Driss and Lacombe, G. and Lanza, Nina and Lapauw, Laurent and Laserna, Javier and Lasue, J. and Le Deit, Laetitia and Le Mouélic, Stéphane and Le Comte, E. and Lee, Qiu-Mei and Legett, IV, C. and Leveille, Richard and Lewin, Eric and Leyrat, C. and Lopez-Reyes, Guillermo and Lorenz, R. and Lucero, Briana and Madariaga, Juan Manuel and Madsen, Soren and Madsen, M. and Mangold, N. and Manni, F. and Mariscal, J.-F. and Martinez-Frias, Jesus and Mathieu, K. and Mathon, R. and McCabe, Kevin P. and McConnochie, T. and McLennan, Scott M. and Mekki, J. and Melikechi, Noureddine and Meslin, Pierre-Yves and Micheau, Y. and Michel, Y. and Michel, John M. and Mimoun, David and Misra, A. and Montagnac, Gilles and Montaron, Christophe and Montmessin, Franck and Moros, J. and Mousset, V. and Morizet, Y. and Murdoch, Naomi and Newell, Raymond T. and Newsom, Horton and Nguyen Tuong, N. and Ollila, Ann M. and Orttner, G. and Oudda, L. and Pares, Laurent and Parisot, Jérôme and Parot, Yann and Pérez, René and Pheav, D. and Picot, L. and Pilleri, Paolo and Pilorget, C. and Pinet, P. and Pont, Gabriel and Poulet, F. and Quantin-Nataf, Cathy and Quertier, Benjamin and Rambaud, D. and Rapin, William and Romano, P. and Roucayrol, L. and Royer, C. and Ruellan, M. and Sandoval, B.F. and Sautter, Violaine and Schoppers, Marcel J. and Schröder, S. and Seran, H.-C. and Sharma, Shiv K. and Sobron, Pablo and Sodki, M. and Sournac, A. and Sridhar, Vishnu and Standarovsky, D. and Storms, Steven and Striebig, Nicolas and Tatat, M. and Toplis, M. and Torre-Fdez, Imanol and Toulemont, N. and Velasco, C. and Veneranda, Marco and Venhaus, Dawn and Virmontois, C. and Viso, M. and Willis, P. and Wong, K.W.},
  journal = {Space Science Reviews},
  volume = {217},
  number = {47},
  year = {2021},
  doi = {10.1007/s11214-021-00807-w},
  abstract = {Abstract On the NASA 2020 rover mission to Jezero crater, the remote determination of the texture, mineralogy and chemistry of rocks is essential to quickly and thoroughly characterize an area and to optimize the selection of samples for return to Earth. As part of the Perseverance payload, SuperCam is a suite of five techniques that provide critical and complementary observations via Laser-Induced Breakdown Spectroscopy (LIBS), Time-Resolved Raman and Luminescence (TRR/L), visible and near-infrared spectroscopy (VISIR), high-resolution color imaging (RMI), and acoustic recording (MIC). SuperCam operates at remote distances, primarily 2–7 m, while providing data at sub-mm to mm scales. We report on SuperCam’s science objectives in the context of the Mars 2020 mission goals and ways the different techniques can address these questions. The instrument is made up of three separate subsystems: the Mast Unit is designed and built in France; the Body Unit is provided by the United States; the calibration target holder is contributed by Spain, and the targets themselves by the entire science team. This publication focuses on the design, development, and tests of the Mast Unit; companion papers describe the other units. The goal of this work is to provide an understanding of the technical choices made, the constraints that were imposed, and ultimately the validated performance of the flight model as it leaves Earth, and it will serve as the foundation for Mars operations and future processing of the data.}
}

Wiens, R. C., Maurice, S., Robinson, S. H., Nelson, A. E., Cais, P., Bernardi, P., Newell, R. T., Clegg, S., Sharma, S. K., Storms, S., Deming, J., Beckman, D., Ollila, A. M., Gasnault, O., Anderson, R. B., André, Y., Angel, S. M., Arana, G., Auden, E., Beck, P., Becker, J., Benzerara, K., Bernard, S., Beyssac, O., Borges, L., Bousquet, B., Boyd, K., Caffrey, M., Carlson, J., Castro, K., Celis, J., Chide, B., Clark, K., Cloutis, E., Cordoba, E. C., Cousin, A., Dale, M., Deflores, L., Delapp, D., Deleuze, M., Dirmyer, M., Donny, C., Dromart, G., Duran, M. G., Egan, M., Ervin, J., Fabre, C., Fau, A., Fischer, W., Forni, O., Fouchet, T., Fresquez, R., Frydenvang, J., Gasway, D., Gontijo, I., Grotzinger, J., Jacob, X., Jacquinod, S., Johnson, J. R., Klisiewicz, R. A., Lake, J., Lanza, N., Laserna, J., Lasue, J., Le Mouélic, S., Legett, I. C., Leveille, R., Lewin, E., Lopez-Reyes, G., Lorenz, R., Lorigny, E., Love, S. P., Lucero, B., Madariaga, J. M., Madsen, M., Madsen, S., Mangold, N., Manrique, J. A., Martinez, J., Martinez-Frias, J., McCabe, K. P., McConnochie, T. H., McGlown, J. M., McLennan, S. M., Melikechi, N., Meslin, P.-Y., Michel, J. M., Mimoun, D., Misra, A., Montagnac, G., Montmessin, F., Mousset, V., Murdoch, N., Newsom, H., Ott, L. A., Ousnamer, Z. R., Pares, L., Parot, Y., Pawluczyk, R., Peterson, C. G., Pilleri, P., Pinet, P., Pont, G., Poulet, F., Provost, C., Quertier, B., Quinn, H., Rapin, W., Reess, J.-M., Regan, A. H., Reyes-Newell, A. L., Romano, P. J., Royer, C., Rull, F., Sandoval, B., Sarrao, J. H., Sautter, V., Schoppers, M. J., Schröder, S., Seitz, D., Shepherd, T., Sobron, P., Dubois, B., Sridhar, V., Toplis, M. J., Torre-Fdez, I., Trettel, I. A., Underwood, M., Valdez, A., Valdez, J., Venhaus, D. and Willis, P. (2021). The SuperCam Instrument Suite on the NASA Mars 2020 Rover: Body Unit and Combined System Tests . Space Science Reviews, 4. Source

BibTeX

@article{wiens2021supercam,
  title = {The SuperCam Instrument Suite on the NASA Mars 2020 Rover: Body Unit and Combined System Tests},
  author = {Wiens, Roger C. and Maurice, Sylvestre and Robinson, Scott H. and Nelson, Anthony E. and Cais, Philippe and Bernardi, Pernelle and Newell, Raymond T. and Clegg, Sam and Sharma, Shiv K. and Storms, Steven and Deming, Jonathan and Beckman, Darrel and Ollila, Ann M. and Gasnault, Olivier and Anderson, Ryan B. and André, Yves and Angel, S. Michael and Arana, Gorka and Auden, Elizabeth and Beck, Pierre and Becker, Joseph and Benzerara, Karim and Bernard, Sylvain and Beyssac, Olivier and Borges, Louis and Bousquet, Bruno and Boyd, Kerry and Caffrey, Michael and Carlson, Jeffrey and Castro, Kepa and Celis, Jorden and Chide, Baptiste and Clark, Kevin and Cloutis, Edward and Cordoba, Elizabeth C. and Cousin, Agnes and Dale, Magdalena and Deflores, Lauren and Delapp, Dorothea and Deleuze, Muriel and Dirmyer, Matthew and Donny, Christophe and Dromart, Gilles and Duran, M. George and Egan, Miles and Ervin, Joan and Fabre, Cecile and Fau, Amaury and Fischer, Woodward and Forni, Olivier and Fouchet, Thierry and Fresquez, Reuben and Frydenvang, Jens and Gasway, Denine and Gontijo, Ivair and Grotzinger, John and Jacob, Xavier and Jacquinod, Sophie and Johnson, Jeffrey R. and Klisiewicz, Roberta A. and Lake, James and Lanza, Nina and Laserna, Javier and Lasue, Jeremie and Le Mouélic, Stéphane and Legett, IV, Carey and Leveille, Richard and Lewin, Eric and Lopez-Reyes, Guillermo and Lorenz, Ralph and Lorigny, Eric and Love, Steven P. and Lucero, Briana and Madariaga, Juan Manuel and Madsen, Morten and Madsen, Soren and Mangold, Nicolas and Manrique, Jose Antonio and Martinez, J.P. and Martinez-Frias, Jesus and McCabe, Kevin P. and McConnochie, Timothy H. and McGlown, Justin M. and McLennan, Scott M. and Melikechi, Noureddine and Meslin, Pierre-Yves and Michel, John M. and Mimoun, David and Misra, Anupam and Montagnac, Gilles and Montmessin, Franck and Mousset, Valerie and Murdoch, Naomi and Newsom, Horton and Ott, Logan A. and Ousnamer, Zachary R. and Pares, Laurent and Parot, Yann and Pawluczyk, Rafal and Peterson, C. Glen and Pilleri, Paolo and Pinet, Patrick and Pont, Gabriel and Poulet, Francois and Provost, Cheryl and Quertier, Benjamin and Quinn, Heather and Rapin, William and Reess, Jean-Michel and Regan, Amy H. and Reyes-Newell, Adriana L. and Romano, Philip J. and Royer, Clement and Rull, Fernando and Sandoval, Benigno and Sarrao, Joseph H. and Sautter, Violaine and Schoppers, Marcel J. and Schröder, Susanne and Seitz, Daniel and Shepherd, Terra and Sobron, Pablo and Dubois, Bruno and Sridhar, Vishnu and Toplis, Michael J. and Torre-Fdez, Imanol and Trettel, Ian A. and Underwood, Mark and Valdez, Andres and Valdez, Jacob and Venhaus, Dawn and Willis, Peter},
  journal = {Space Science Reviews},
  volume = {217},
  number = {4},
  pages = {4--4},
  year = {2021},
  doi = {10.1007/s11214-020-00777-5},
  abstract = {Abstract The SuperCam instrument suite provides the Mars 2020 rover, Perseverance, with a number of versatile remote-sensing techniques that can be used at long distance as well as within the robotic-arm workspace. These include laser-induced breakdown spectroscopy (LIBS), remote time-resolved Raman and luminescence spectroscopies, and visible and infrared (VISIR; separately referred to as VIS and IR) reflectance spectroscopy. A remote micro-imager (RMI) provides high-resolution color context imaging, and a microphone can be used as a stand-alone tool for environmental studies or to determine physical properties of rocks and soils from shock waves of laser-produced plasmas. SuperCam is built in three parts: The mast unit (MU), consisting of the laser, telescope, RMI, IR spectrometer, and associated electronics, is described in a companion paper. The on-board calibration targets are described in another companion paper. Here we describe SuperCam’s body unit (BU) and testing of the integrated instrument. The BU, mounted inside the rover body, receives light from the MU via a 5.8 m optical fiber. The light is split into three wavelength bands by a demultiplexer, and is routed via fiber bundles to three optical spectrometers, two of which (UV and violet; 245–340 and 385–465 nm) are crossed Czerny-Turner reflection spectrometers, nearly identical to their counterparts on ChemCam. The third is a high-efficiency transmission spectrometer containing an optical intensifier capable of gating exposures to 100 ns or longer, with variable delay times relative to the laser pulse. This spectrometer covers 535–853 nm ( $105\text{--}7070~\text{cm}^{-1}$ 105 – 7070 cm − 1 Raman shift relative to the 532 nm green laser beam) with $12~\text{cm}^{-1}$ 12 cm − 1 full-width at half-maximum peak resolution in the Raman fingerprint region. The BU electronics boards interface with the rover and control the instrument, returning data to the rover. Thermal systems maintain a warm temperature during cruise to Mars to avoid contamination on the optics, and cool the detectors during operations on Mars. Results obtained with the integrated instrument demonstrate its capabilities for LIBS, for which a library of 332 standards was developed. Examples of Raman and VISIR spectroscopy are shown, demonstrating clear mineral identification with both techniques. Luminescence spectra demonstrate the utility of having both spectral and temporal dimensions. Finally, RMI and microphone tests on the rover demonstrate the capabilities of these subsystems as well.}
}

Wiens, R. C., Maurice, S., Barraclough, B., Saccoccio, M., Barkley, W. C., Bell, I. J. F., Bender, S., Bernardin, J., Blaney, D., Blank, J., Bouyé, M., Bridges, N., Bultman, N., Caïs, P., Clanton, R. C., Clark, B., Clegg, S., Cousin, A., Cremers, D., Cros, A., DeFlores, L., Delapp, D., Dingler, R., D'Uston, C., Dyar, M. D., Elliott, T., Enemark, D., Fabre, C., Flores, M., Forni, O., Gasnault, O., Hale, T., Hays, C., Herkenhoff, K., Kan, E., Kirkland, L., Kouach, D., Landis, D., Langevin, Y., Lanza, N., LaRocca, F., Lasue, J., Latino, J., Limonadi, D., Lindensmith, C., Little, C., Mangold, N., Manhes, G., Mauchien, P., McKay, C., Miller, E., Mooney, J., Morris, R. V., Morrison, L., Nelson, T., Newsom, H., Ollila, A., Ott, M., Pares, L., Perez, R., Poitrasson, F., Provost, C., Reiter, J. W., Roberts, T., Romero, F., Sautter, V., Salazar, S., Simmonds, J. J., Stiglich, R., Storms, S., Striebig, N., Thocaven, J.-J., Trujillo, T., Ulibarri, M., Vaniman, D., Warner, N., Waterbury, R., Whitaker, R., Witt, J. and Wong-Swanson, B. (2012). The ChemCam Instrument Suite on the Mars Science Laboratory (MSL) Rover: Body Unit and Combined System Tests . Space Science Reviews. Source

BibTeX

@article{wiens2012chemcam,
  title = {The ChemCam Instrument Suite on the Mars Science Laboratory (MSL) Rover: Body Unit and Combined System Tests},
  author = {Wiens, Roger C. and Maurice, Sylvestre and Barraclough, Bruce and Saccoccio, Muriel and Barkley, Walter C. and Bell, III, James F. and Bender, Steve and Bernardin, John and Blaney, Diana and Blank, Jennifer and Bouyé, Marc and Bridges, Nathan and Bultman, Nathan and Caïs, Phillippe and Clanton, Robert C. and Clark, Benton and Clegg, Samuel and Cousin, Agnes and Cremers, David and Cros, Alain and DeFlores, Lauren and Delapp, Dorothea and Dingler, Robert and D'Uston, Claude and Dyar, M. Darby and Elliott, Tom and Enemark, Don and Fabre, Cecile and Flores, Mike and Forni, Olivier and Gasnault, Olivier and Hale, Thomas and Hays, Charles and Herkenhoff, Ken and Kan, Ed and Kirkland, Laurel and Kouach, Driss and Landis, David and Langevin, Yves and Lanza, Nina and LaRocca, Frank and Lasue, Jeremie and Latino, Joseph and Limonadi, Daniel and Lindensmith, Chris and Little, Cynthia and Mangold, Nicolas and Manhes, Gerard and Mauchien, Patrick and McKay, Christopher and Miller, Ed and Mooney, Joe and Morris, Richard V. and Morrison, Leland and Nelson, Tony and Newsom, Horton and Ollila, Ann and Ott, Melanie and Pares, Laurent and Perez, René and Poitrasson, Franck and Provost, Cheryl and Reiter, Joseph W. and Roberts, Tom and Romero, Frank and Sautter, Violaine and Salazar, Steven and Simmonds, John J. and Stiglich, Ralph and Storms, Steven and Striebig, Nicolas and Thocaven, Jean-Jacques and Trujillo, Tanner and Ulibarri, Mike and Vaniman, David and Warner, Noah and Waterbury, Rob and Whitaker, Robert and Witt, James and Wong-Swanson, Belinda},
  journal = {Space Science Reviews},
  volume = {170},
  pages = {167--227},
  year = {2012},
  doi = {10.1007/s11214-012-9902-4},
  abstract = {The ChemCam instrument suite on the Mars Science Laboratory (MSL) rover Curiosity provides remote compositional information using the first laser-induced breakdown spectrometer (LIBS) on a planetary mission, and provides sample texture and morphology data using a remote micro-imager (RMI). Overall, ChemCam supports MSL with five capabilities: remote classification of rock and soil characteristics; quantitative elemental compositions including light elements like hydrogen and some elements to which LIBS is uniquely sensitive (e.g., Li, Be, Rb, Sr, Ba); remote removal of surface dust and depth profiling through surface coatings; context imaging; and passive spectroscopy over the 240–905 nm range. ChemCam is built in two sections: The mast unit, consisting of a laser, telescope, RMI, and associated electronics, resides on the rover’s mast, and is described in a companion paper. ChemCam’s body unit, which is mounted in the body of the rover, comprises an optical demultiplexer, three spectrometers, detectors, their coolers, and associated electronics and data handling logic. Additional instrument components include a 6 m optical fiber which transfers the LIBS light from the telescope to the body unit, and a set of onboard calibration targets. ChemCam was integrated and tested at Los Alamos National Laboratory where it also underwent LIBS calibration with 69 geological standards prior to integration with the rover. Post-integration testing used coordinated mast and instrument commands, including LIBS line scans on rock targets during system-level thermal-vacuum tests. In this paper we describe the body unit, optical fiber, and calibration targets, and the assembly, testing, and verification of the instrument prior to launch.}
}

Topper, A. D., Lauenstein, J.-M., Wilcox, E. P., Berg, M. D., Campola, M. J., Casey, M. C., Wyrwas, E. J., O'Bryan, M. V., Carstens, T. A., Fedele, C. M., Forney, J. D., Kim, H. S., Osheroff, J. M., Phan, A. M., Chaiken, M. F., Cochran, D. J., Pellish, J. A. and Majewicz, P. J. (2020). NASA Goddard Space Flight Center's Compendium of Radiation Effects Test Results . IEEE Radiation Effects Data Workshop. Source

BibTeX

@inproceedings{topper2020nasa,
  title = {NASA Goddard Space Flight Center's Compendium of Radiation Effects Test Results},
  author = {Topper, Alyson D. and Lauenstein, Jean-Marie and Wilcox, Edward P. and Berg, Melanie D. and Campola, Michael J. and Casey, Megan C. and Wyrwas, Edward J. and O'Bryan, Martha V. and Carstens, Thomas A. and Fedele, Caroline M. and Forney, James D. and Kim, Hak S. and Osheroff, Jason M. and Phan, Anthony M. and Chaiken, Max F. and Cochran, Donna J. and Pellish, Jonathan A. and Majewicz, Peter J.},
  booktitle = {IEEE Radiation Effects Data Workshop},
  pages = {1--12},
  year = {2020},
  doi = {10.1109/redw51883.2020.9325841},
  abstract = {Total ionizing dose, displacement damage dose, and single event effects testing were performed to characterize and determine the suitability of candidate electronics for NASA space utilization. Devices tested include FETs, flash memory, FPGAs, optoelectronics, digital, analog, and bipolar devices.}
}

Whittaker, C. (2021). MR-AVI-0068 Radiation Survival Summary, Revision A . Carnegie Mellon University, MoonRanger Project. Source

BibTeX

@techreport{whittaker2021radiation,
  title = {MR-AVI-0068 Radiation Survival Summary, Revision A},
  author = {Whittaker, Chuck},
  institution = {Carnegie Mellon University, MoonRanger Project},
  month = {May},
  year = {2021},
  url = {https://labs.ri.cmu.edu/moonranger/wp-content/uploads/sites/24/2021/07/MR-AVI-0068_Radiation-Survival-Summary.pdf}
}

Berger, L. N. and Bell, C. (2020). Comparing Cumulative Flight Thermal Fatigue to Ground Test Results for Memory Components on the Mars Curiosity Rover . AIAA Science and Technology Forum and Exposition. Source

BibTeX

@inproceedings{berger2020comparing,
  title = {Comparing Cumulative Flight Thermal Fatigue to Ground Test Results for Memory Components on the Mars Curiosity Rover},
  author = {Berger, Lindsey N and Bell, Charles},
  booktitle = {AIAA Science and Technology Forum and Exposition},
  publisher = {JPL Open Repository},
  year = {2020},
  url = {https://dataverse.jpl.nasa.gov/dataset.xhtml?persistentId=hdl:2014/52311}
}

Allen, G. R., Guertin, S. M., Scheick, L. Z., Irom, F. and Zajac, S. (2012). Compendium of recent test results of single event effects conducted by the Jet Propulsion Laboratory . IEEE Radiation Effects Data Workshop. Source

BibTeX

@inproceedings{allen2012compendium,
  title = {Compendium of recent test results of single event effects conducted by the Jet Propulsion Laboratory},
  author = {Allen, Gregory R. and Guertin, Steven M. and Scheick, Leif Z. and Irom, Farokh and Zajac, Stephanie},
  booktitle = {IEEE Radiation Effects Data Workshop},
  pages = {1-10},
  publisher = {IEEE},
  year = {2012},
  doi = {10.1109/redw.2012.6353747},
  abstract = {This paper reports heavy ion, proton, and laser induced single event effects results for a variety of microelectronic devices targeted for possible use in NASA spacecrafts. The compendium covers devices tested within the years of 2010 through 2012.}
}

McClure, S. S., Allen, G. R., Irom, F., Scheick, L. Z., Adell, P. C. and Miyahira, T. F. (2010). Compendium of test results of recent single event effect tests conducted by the Jet Propulsion Laboratory . IEEE Radiation Effects Data Workshop. Source

BibTeX

@inproceedings{mcclure2010compendium,
  title = {Compendium of test results of recent single event effect tests conducted by the Jet Propulsion Laboratory},
  author = {McClure, Steven S. and Allen, Gregory R. and Irom, Farokh and Scheick, Leif Z. and Adell, Philippe C. and Miyahira, Tetsuo F.},
  booktitle = {IEEE Radiation Effects Data Workshop},
  pages = {6-6},
  publisher = {IEEE},
  year = {2010},
  doi = {10.1109/redw.2010.5619495},
  abstract = {This paper reports heavy ion and proton-induced single event effect (SEE) results from recent tests for a variety of microelectronic devices. The compendium covers devices tested over the last two years by the Jet Propulsion Laboratory.}
}

Amrbar, M. and Guertin, S. M. (2016). Total Ionizing Dose response of SDRAM, DDR2 and DDR3 memories . IEEE Radiation Effects Data Workshop (REDW). Source

BibTeX

@inproceedings{amrbar2016total,
  title = {Total Ionizing Dose response of SDRAM, DDR2 and DDR3 memories},
  author = {Amrbar, Mehran and Guertin, Steven M.},
  booktitle = {IEEE Radiation Effects Data Workshop (REDW)},
  pages = {1-6},
  publisher = {IEEE},
  year = {2016},
  doi = {10.1109/nsrec.2016.7891750},
  abstract = {Total Ionizing Dose response of SDRAM, DDR2 and DDR3 memories is reported in static bias, and auto refresh modes. Data analysis reveals some types of memory have significant increases in stuck bits during TID exposure when refreshed.}
}

Blake, J. B. and Mandel, R. (1987). On-Orbit Observations of Single-Event Upset in Harris HM-6508 1K RAMs . The Aerospace Corporation for USAF Space Division, SD-TR-86-99 (TR-0086(6940-05)-11, Reissue A). Source

BibTeX

@techreport{blake1987orbit,
  title = {On-Orbit Observations of Single-Event Upset in Harris HM-6508 1K RAMs},
  author = {Blake, J. Bernard and Mandel, R.},
  volume = {33},
  number = {SD-TR-86-99 (TR-0086(6940-05)-11, Reissue A)},
  pages = {1616-1619},
  institution = {The Aerospace Corporation for USAF Space Division},
  year = {1987},
  doi = {10.1109/tns.1986.4334651},
  abstract = {The SEU and latchup rate of a satellite subsystem containing 384 Harris HM-6508 RAMs was observed over a 2 year period. The satellite was in a low polar orbit. A total of 47 single SEUs, 9 double, 1 triple and 1 quadruple events were observed; the multiple events were 19% of the total. No latchup was observed. The error rate was 7.6 × 10-2 SEUs/chip-year and an upper limit was found of the ratio of latchups/SEUs of 1.7 × 10-2. The observed SEU rate was consistent with predictions based upon laboratory test, using the Lawrence Berkeley Laboratory 88" cyclotron.}
}

Ladbury, R., Reed, R. A., Marshall, P. W., LaBel, K. A., Anantaraman, R., Fox, R., Sanderson, D. P., Stolz, A., Yurkon, J., Zeller, A. F. and Stetson, J. W. (2004). Performance of the High-Energy Single-Event Effects Test Facility (SEETF) at Michigan State University's National Superconducting Cyclotron Laboratory (NSCL) . IEEE Transactions on Nuclear Science, 20040171458. Source

BibTeX

@article{ladbury2004performance,
  title = {Performance of the High-Energy Single-Event Effects Test Facility (SEETF) at Michigan State University's National Superconducting Cyclotron Laboratory (NSCL)},
  author = {Ladbury, R. and Reed, R. A. and Marshall, Paul W. and LaBel, Kenneth A. and Anantaraman, R. and Fox, R. and Sanderson, D. P. and Stolz, A. and Yurkon, J. and Zeller, A. F. and Stetson, J. W.},
  journal = {IEEE Transactions on Nuclear Science},
  volume = {51},
  number = {20040171458},
  pages = {3664-3668},
  institution = {NASA},
  address = {Atlanta, Georgia},
  year = {2004},
  doi = {10.1109/tns.2004.839300},
  abstract = {The performance of Michigan State University's Single-Event Effects Test Facility (SEETF) during its inaugural runs is evaluated. Beam profiles and other diagnostics are presented, and prospects for future development and testing are discussed.}
}