Avionics
A parts database of components selected, qualified, or flown by planetary and orbital robotics programs, each with the citation that establishes it. The purpose is reuse: a designer choosing a processor, motor, encoder, sensor, or FPGA can see what has already been through a space qualification campaign and what the campaign found. A component with no published flight or qualification result is not listed.
Where the part-level record now reaches
Section titled “Where the part-level record now reaches”Batteries, power electronics and inertial sensors each carry at least one published part-level result. The lithium-ion cell behind the Mars Exploration Rover battery has a JPL qualification campaign [5], and heavy-ion burnout and latchup results exist for GaN and silicon power devices [6]; both are on Power and Batteries. A commercial MEMS accelerometer has a heavy-ion latchup screen whose cross-section moves with temperature [7], on Sensors and IMUs.
Several further named parts in those classes carry a performance figure but no qualification campaign, and they are listed as such on their pages. A NASA COMPASS design study assumes a Saft VES16 cell for a Venus orbiter battery at 90 percent maximum depth of discharge, alongside a TERMA power equipment box with BCDU and ARU cards [1]; the cell was an assumption in a study and the vehicle did not fly. The one named motor controller is the Elmo Motion Control G-Sol WHI20/100, closing position and velocity loops directly off the actuator feedback sensors on the RASSOR 2.0 ground prototype [2]. SPHERES uses three Honeywell QA-T160 single-axis accelerometers, quoted at better than 5 micro-g resolution, and three BEI Gyrochip II rate gyros from Systron Donner measuring to plus or minus 50 degrees per second on a vibrating quartz tuning fork element [4]. The later SPHERES documentation reproduces Honeywell QA-750 and QA-75C datasheets in its appendices [3], which are vendor material rather than a qualification record. RASSOR 2.0 carries an Xsens MTI-30-2A5G4-O [2]. No star tracker flown on a planetary robot is published down to a part number.
Radios, transponders and antennas carry part-level results of their own, on Radios and Antennas, together with the radio-frequency and data interface parts screened at a named beam. Three results there are part-level: a Ka-band deployable antenna whose flight-model gain was measured after deployment, after vibration and after thermal vacuum; a rover UHF radio measured at the box level in a system thermal vacuum test; and laboratory receiver sensitivity thresholds for the Ingenuity to Perseverance link.
What the component record is made of
Section titled “What the component record is made of”The parts that fly on planetary and orbital robots are chosen under three constraints that a terrestrial designer does not carry together: a radiation environment that can destroy a commercial part outright, a thermal and mechanical life that is longer than any laboratory duty cycle, and a mass and power budget that rules out most hardened parts. Three bodies of evidence answer them, and they differ in what they can support.
Radiation screening is the largest. JPL compendia report single event effect results on roughly forty parts tested between 2007 and 2010 [12] and on a later generation covering FPGAs, processors, NAND flash and power MOSFETs [11]. The most consequential result in the later compendium is a destructive latch in the Linear Technology LTC1419 ADC that flew on Mars Science Laboratory, and that latch depends on temperature [11]. Heavy-ion screening of fourteen commercial parts for a Class D payload found four that latch destructively, one of them a buck regulator that fails permanently at LET 42.8 MeV-cm2/mg [7]. That test covers latchup only, and the highest LET available is below the customary heavy-ion qualification point [7]. Test method has its own reference: for system-on-chip devices the per-structure approach fails because the part is a whole computer, and the JPL guideline defines effective sensitivity as the smallest cross section a setup could have detected [13]. The facility behind much of this work reproduces most of the space LET and energy range above LET 3 MeV-cm2/mg with ions of 60 to 143 MeV per nucleon [20].
Total dose is treated separately. Comparator transient and dose results show that sensitivity is set by the application bias and not by the part alone [17]. Europa Clipper candidates were irradiated to 300 krad(Si), with dose rate and bias dependence recorded part by part [18], and six candidate devices irradiated under flight bias and mission dose rates showed that a manufacturer rating can be optimistic by a large factor [19]. A planetary micro rover on a short lunar mission takes a different route: 2.5 mm aluminum shells around unqualified boards, a total dose near half a krad, and current monitoring for latchup [15].
Flight data checks the ground predictions less often than it should. Twenty ISS command and data handling computers give 12 years of upset counts, and the comparison shows that conventional ground qualification overpredicted real orbital rates [14]. For Mars surface hardware the closest comparison is thermal fatigue: the flash memory in the Curiosity Rover Compute Element failed to mount three times, and the accumulated flight cycles were too few to explain the first failure, which points to a piece-part defect or workmanship and not to the accelerated-life model [16].
Families of component and what each has flown
Section titled “Families of component and what each has flown”Motors and actuators. The Apollo lunar roving vehicle used a four-pole brush series motor through an 80:1 harmonic drive, sealed in dry nitrogen and lubricated with Krytox 143AZ, derived from a vehicle requirement chain down to shaft torque-speed points [29]. A 1987 survey compared ten transmission families for space manipulators by backlash, stiffness, backdrivability and efficiency [30]. A commercial maxon brushless motor reached Mars 2020 after an upscreening campaign for ten Sample Caching System locations and the Ingenuity deployment arm; the campaign found a stray flux problem in which the detent magnet corrupted Hall sensor switching [10]. The ISRU Pilot Excavator uses one actuator design for wheel, arm and drum, a ThinGap LSI 75-12 motor with a Harmonic Drive CSF gearset [8], and its qualification ran four tests in a dynamometer and produced a current-torque-speed-temperature model for flight use [9]. These are ground-qualified for a lunar mission that has not flown.
Processors, memory and logic. A Snapdragon 855 benchmark pairs named space workloads with measured runtime and power on the CPU, GPU and DSP [27], while a stereo pipeline in a single Virtex-4 LX160 FPGA ran 1024 by 768 pairs at 15 Hz [28]. The two reach opposite conclusions on where stereo should run, and neither is a flight configuration of a rover in those references. Dedicated pages cover Processors, Memory and Storage and FPGAs and Logic.
Imagers and optics. Mastcam-Z on Perseverance uses a KAI-2020CM CCD with 1600 by 1200 pixels of 7.4 micron pitch, and its radiation qualification is a monitoring plan for hot pixels, not a published dose number [21]. SuperCam’s mast unit points open loop to plus or minus 9.5 mrad (2 sigma) per axis and relies on closed-loop imager feedback for the science requirement [22]. See Imagers and Optics.
Radio and communications. The planned Mars Science Laboratory UHF and X-band architecture [24] and the Mars Exploration Rover telecom record, where relay through orbiters carried most of the returned data [25], give the as-planned and as-flown pair. The Queqiao relay in an Earth-Moon L2 halo orbit sets the forward and return rate limits that govern Yutu-2 operations [26]. See Radios and Antennas.
Free-flyer docking hardware. The SPHERES docking port and optical relative sensor are documented with an accuracy requirement and an approach velocity threshold below which capture is reliable [32]. They were tested on the ISS, not on a planetary surface.
Mobility statistics bear on actuator and processor selection indirectly. Curiosity drove 21,318.5 m over 738 attempted drives in seven years, and visual odometry converged in 99.55 percent of its attempts [23]. The long-duration exposure record of the Long Duration Exposure Facility finds no system anomaly attributable to long LEO exposure, and it is the main source here on cold welding, dry film lubricants and seals after 69 months in orbit [31]. A NASA lunar dust catalog is the contextual source on what Apollo hardware found in abrasion and seal contamination, though the edition held is the superseded first one [33].
What is not established
Section titled “What is not established”Most part-level results are ground screening of a lot, a bias and a beam, and they do not transfer to another lot, voltage or dose rate [7][19]. Where a part flew, the published record usually gives the part number and the mission but not the qualification data, as with the Mastcam-Z CCD [21]. The Class D heavy-ion screening has no single event upset, functional interrupt or total dose data and no rate calculation [7]. The IPEx actuators were tested at 1 g only, and the arm and bucket drum fourth tests reused hardware for schedule reasons [8]. The Saft VES16 cell in the COMPASS Venus orbiter study is a study input, not flown parts [1]. No star tracker flown on a planetary robot is published down to a part number.
References
- Hunter, G. W., Izenberg, N., Oleson, S. R., Newman, J. M., Gilmore, M., Jessup, K. L., Herrick, R., Balcerski, J., Colozza, A., Faller, B., Fincannon, J., Fittje, J., Gyekenyesi, J., Jones, R., Klefman, B., Landis, G., Martini, M., McCarty, S., Packard, T., Smith, D. and Turnbull, E. (2020). Compass Final Report: Venus Bridge Orbiter and Surface Study (V-BOSS)
. NASA Glenn Research Center, NASA/TP-2020-220152. Source
BibTeX
@techreport{hunter2020compass, title = {Compass Final Report: Venus Bridge Orbiter and Surface Study (V-BOSS)}, author = {Hunter, Gary W. and Izenberg, Noam and Oleson, Steven R. and Newman, J. M. and Gilmore, Martha and Jessup, Kandis Lea and Herrick, Robert and Balcerski, Jeffrey and Colozza, Anthony and Faller, Brent and Fincannon, James and Fittje, James and Gyekenyesi, John and Jones, Robert and Klefman, Brandon and Landis, Geoffrey and Martini, Michael and McCarty, Steven and Packard, Thomas and Smith, David and Turnbull, Elizabeth}, number = {NASA/TP-2020-220152}, institution = {NASA Glenn Research Center}, year = {2020}, url = {https://ntrs.nasa.gov/citations/20200013062}, abstract = {The Venus Bridge Orbiter and Surface Study (V-BOSS) Compass concurrent engineering design team study shows that new, high-priority Venus science can be achieved using a linked Orbiter + Surface Element (Lander) mission concept within a $200M cost cap with assumptions. This is feasible through optimizing investment in early technologies and platforms, such as the Long-Lived In-Situ Solar System Explorer (LLISSE), leveraging known and flight-ready technology, and the overall use of simple, small, robust systems in innovative approaches to Venus exploration. This architecture allows a range of science investigations through modification of Orbiter-Lander platforms in this study through choice of other instruments (often sensors), science themes, or operational modes. In particular, a fundamental strength of this approach is to provide science not available in other ways by using simplified architectures including rugged systems operable in-situ on the Venus surface. Such investigations would be pathfinders for more complex, and more expensive, future missions. Additionally, the results of this study can be used to further champion the need, value and return of early investment technology programs for the hard problem of in-situ investigations at Venus.} } - Mueller, R. P., Smith, J. D., Schuler, J. M., Nick, A. J., Gelino, N. J., Leucht, K. W., Townsend, I. I. and Dokos, A. G. (2016). Design of an Excavation Robot: Regolith Advanced Surface Systems Operations Robot (RASSOR) 2.0
. ASCE Earth and Space Conference, 20210011366. Source
BibTeX
@inproceedings{mueller2016design, title = {Design of an Excavation Robot: Regolith Advanced Surface Systems Operations Robot (RASSOR) 2.0}, author = {Mueller, Robert P. and Smith, Jonathan D. and Schuler, Jason M. and Nick, Andrew J. and Gelino, Nathan J. and Leucht, Kurt W. and Townsend, Ivan I. and Dokos, Adam G.}, booktitle = {ASCE Earth and Space Conference}, number = {20210011366}, pages = {163-174}, institution = {NASA}, year = {2016}, doi = {10.1061/9780784479971.018}, abstract = {To continue on a sustainable and flexible path, NASA needs to address the challenge of collecting and moving large amounts of regolith at the destination. Acquiring the water resources on Mars will require mining significant quantities of regolith, and this is not possible with the state-of-the-art low mass excavation systems. Low gravity environments (Mars = 3/8G) and launch mass restrictions limit the traction and the resulting reaction force of the vehicle, making current terrestrial techniques impractical. This project addressed this challenge by developing a completely new technology that can mine large quantities of regolith on Mars. Recent measurements by the “Curiosity” rover on Mars have found that the regolith contains ~2% water by weight globally, ~4% in Jezero Crater (Human Architecture Team’s reference landing site), and much more at the poles. RASSOR 2.0 is a planetary excavator, which has a mass of 66 kg, with a 0.38 kg vehicle mass per kilogram, per hour of excavation rate and power usage of 4 W per kg of regolith excavation rate. A single RASSOR 2.0 can excavate a minimum of 2.7 metric tons of regolith per day. This is accomplished by using counteracting excavation forces on two opposing digging implements called bucket drums and an autonomous mining control system. This work has addressed several major research areas outlined in the NASA Technology Area (TA) 04 Robotics and Autonomous Systems and TA 07 Human Destination Systems roadmaps. This project started at Technology Readiness Level (TRL) 4 as a low fidelity “proof of concept” prototype which has successfully demonstrated basic regolith simulant excavation functionality in a lab-scale gravity off load test. The foundational technology described here was awarded US patent number: US 9027265 for a “Zero horizontal reaction force excavator” on May 12, 2015.} } - Nolet, S. (2007). Development of a Guidance, Navigation and Control Architecture and Validation Process Enabling Autonomous Docking to a Tumbling Satellite. Source
BibTeX
@phdthesis{nolet2007development, title = {Development of a Guidance, Navigation and Control Architecture and Validation Process Enabling Autonomous Docking to a Tumbling Satellite}, author = {Nolet, Simon}, school = {Massachusetts Institute of Technology}, type = {Ph.D. thesis}, year = {2007}, url = {https://dspace.mit.edu/handle/1721.1/38598} } - Hilstad, M. O. (2002). A Multi-Vehicle Testbed and Interface Framework for the Development and Verification of Separated Spacecraft Control Algorithms. Source
BibTeX
@mastersthesis{hilstad2002multi, title = {A Multi-Vehicle Testbed and Interface Framework for the Development and Verification of Separated Spacecraft Control Algorithms}, author = {Hilstad, Mark O.}, school = {Massachusetts Institute of Technology}, type = {S.M. thesis}, year = {2002}, url = {https://dspace.mit.edu/handle/1721.1/16738} } - Smart, M. C., Ratnakumar, B. V., Ewell, R. C., Whitcanack, L. D., Chin, K. B. and Surampudi, S. (2004). Validation of Lithium-ion cell technology for JPL's 2003 Mars Exploration Rover Mission
. International Energy Conversion Engineering Conference. Source
BibTeX
@inproceedings{smart2004validation, title = {Validation of Lithium-ion cell technology for JPL's 2003 Mars Exploration Rover Mission}, author = {Smart, Marshall C. and Ratnakumar, Bugga V. and Ewell, R. C. and Whitcanack, L. D. and Chin, Keith B. and Surampudi, S.}, booktitle = {International Energy Conversion Engineering Conference}, publisher = {American Institute of Aeronautics and Astronautics}, year = {2004}, doi = {10.2514/6.2004-5764}, abstract = {n early 2004 JPL successfully landed two Rovers, named Spirit and Opportunity, on the surface of Mars after traveling >300 million miles over a 6-7 month period. In order to operate for extended duration on the surface of Mars, both Rovers are equipped with rechargeable Lithium-ion batteries, which were designed to aid in the launch, correct anomalies during cruise, and support surface operations in conjunction with a triple-junction deployable solar arrays. The requirements of the Lithium-ion battery include the ability to provide power at least 90 sols on the surface of Mars, operate over a wide temperature range (-20 C to +40 C), withstanding long storage periods (e.g., cruise period), operate in an inverted position, and support high currents (e.g., firing pyro events). In order to determine the viability of Lithium-ion technology to meet these stringent requirements, a comprehensive test program was implemented aimed at demonstrating the performance capability of prototype cells fabricated by Lithion, Inc. (Yardney Technical Products, Inc.). The testing performed includes, determining the (a) room temperature cycle life, (b) pulse capability as a function of temperature, (e) self-discharge and storage characteristics mission profile capability, (f) cycle life under mission simulation conditions, (g) impedance characteristics, (h) impact of cell orientation, and (i) performance in 8-cell engineering batteries. As will be discussed, the Lithium-ion prototype cells and batteries were demonstrated to meet, as well as, exceed the requirements defined by the mission.} } - 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.} } - Daniel, A. C. and Allen, G. R. (2018). Heavy-Ion Test Results of Several Commercial Components for Use in a JPL Class D Interplanetary Mission Payload
. JPL Open Repository. Source
BibTeX
@inproceedings{daniel2018heavy, title = {Heavy-Ion Test Results of Several Commercial Components for Use in a JPL Class D Interplanetary Mission Payload}, author = {Daniel, Andrew C. and Allen, Gregory R.}, publisher = {JPL Open Repository}, year = {2018}, url = {https://dataverse.jpl.nasa.gov/dataset.xhtml?persistentId=hdl:2014/48478} } - Schuler, J. M., Smith, J. D., Nick, A. J., Buckles, B. C., Dyas, J. E., Ortega, V. V., Cloud, J. M., Dokos, A. G., Zhang, E. L., Wang, J. J., Baron, M. A., Muller, T. J., Clark, C. J. and Howe, M. W. (2024). ISRU Pilot Excavator (IPEx) Technology Readiness Level 5 Design Overview
. AIAA AVIATION Forum and ASCEND, 20240008162. Source
BibTeX
@inproceedings{schuler2024isru, title = {ISRU Pilot Excavator (IPEx) Technology Readiness Level 5 Design Overview}, author = {Schuler, Jason M. and Smith, Jonathan D. and Nick, Andrew J. and Buckles, Bradley C. and Dyas, Jeffrey E. and Ortega, Victoria V. and Cloud, Joseph M. and Dokos, Adam G. and Zhang, Elizabeth L. and Wang, Jerry J. and Baron, Michael A. and Muller, Thomas J. and Clark, Casey J. and Howe, Musashi W.}, booktitle = {AIAA AVIATION Forum and ASCEND}, number = {20240008162}, institution = {NASA}, year = {2024}, doi = {10.2514/6.2024-4890}, abstract = {This paper details the mechanical and mechatronic design of the Technology Readiness Level (TRL)-5 In-Situ Resource Utilization (ISRU) Pilot Excavator (IPEx). IPEx is a robotic excavator designed for a technology demonstration of regolith mining in the lunar south pole region. The novel design uses pairs of counter-acting excavation tools called bucket drums, that dig at the same time in opposing directions to reduce the reaction force needed, thereby enabling mining with a small, low-mass, robotic system. IPEx builds on the prior work of the Regolith Advanced Surface Systems Operations Robot (RASSOR), which is the TRL-4 implementation of this concept. The TRL-5 IPEx subsystems that are discussed in this paper include: Regolith Delivery Subsystem (RDS), Mobility Subsystem (MS), Cameras and Dust Mitigation Subsystem (CDMS), and Thermal Control Subsystem (TCS). Each subsystem is described in detail with rationale for design selections. Dust tolerance is a key feature for IPEx, and this paper details a thermal control system with an actuated radiator cover and phase change material as well as camera modules with removable electrodynamic dust shields (EDS). Additional components such as actuators, wheels, and bucket drums are discussed in detail. Due to their complexity, the avionics and software subsystems will be discussed in a separate publication.} } - Clark, C. J., Smith, J. D., Nick, A. J., Ortega, V. V., Schuler, J. M., Dyas, J. E. and Lahl, J. (2025). Design and Testing of TRL5 IPEx Actuators
. IEEE Aerospace Conference, 20250000003. Source
BibTeX
@inproceedings{clark2025design, title = {Design and Testing of TRL5 IPEx Actuators}, author = {Clark, Casey J. and Smith, Jonathan Drew and Nick, Andrew J. and Ortega, Victoria V. and Schuler, Jason M. and Dyas, Jeffrey E. and Lahl, John}, booktitle = {IEEE Aerospace Conference}, number = {20250000003}, institution = {NASA}, address = {Big Sky, MT}, year = {2025}, url = {https://ntrs.nasa.gov/citations/20250000003}, abstract = {NASA is advancing In-Situ Resource Utilization (ISRU) by focusing on missions aimed at establishing sustainable infrastructure on the Moon and Mars. On the Moon, regolith serves as the most abundant resource. To support ISRU objectives, a 30-kg-class robot called ISRU Pilot Excavator (IPEx) is being developed to excavate 10,000 kg of lunar regolith during a future technology demonstration mission. IPEx uses novel excavation tools, called bucket drums, which are hollow cylinders with scoops staggered around the outside. Regolith is collected with the scoops and flows into the drum where it is captured by an internal baffle system. The excavator can then transport the regolith in the drum and reverse the direction of the drum rotation to dispense the regolith out. IPEx uses two sets of bucket drums that dig simultaneously in opposing directions and results in counteracting excavation forces. This combination of bucket drum excavation tools and counteracting excavation forces enables low mass robotic excavators to effectively dig in reduced gravity environments. This is a significant departure from terrestrial excavators that rely on high mass to produce tractive forces to counteract the forces of excavation. IPEx is made up of several custom actuators that all need to be verified for their intended application. This paper focuses on the initial design, testing and modifications of three actuators: the mobility actuator, the shoulder actuator, and the excavation actuator. Each actuator was tested under four separate test profiles: ambient motor characterization, hot and cold motor characterization, accelerated life test (ALT), and concept of operations (ConOps) test. The motor characterization tests enabled derivation of torque equations for each actuator to estimate output torque without implementing sensors. The accelerated life tests were successful for each actuator and verified the motors’ ability to survive the mission. For the ConOps test, only the bucket drum actuator performed a complete ConOps without the need to restart the test. Overall, the first series of testing resulted in various failure modes and minor design alterations for each actuator. The test results, failure modes, and design alterations are highlighted within this paper. This paper focuses on discussing the mobility, excavation, and shoulder actuator design, testing principles, and results that qualified it as a TRL 5 system.} } - Loschiavo, M., Phillips, R., Mikhaylov, R. and Braunschweig, L. (2020). Mars 2020 Maxon Commercial Motor Development from COTS to Flight Qualified Motors, Gearbox, and Detent Brake: Issues Overcome and Lessons Learned
. Aerospace Mechanisms Symposium. Source
BibTeX
@inproceedings{loschiavo2020mars, title = {Mars 2020 Maxon Commercial Motor Development from COTS to Flight Qualified Motors, Gearbox, and Detent Brake: Issues Overcome and Lessons Learned}, author = {Loschiavo, Michael and Phillips, Robin and Mikhaylov, Rebecca and Braunschweig, Lynn}, booktitle = {Aerospace Mechanisms Symposium}, publisher = {JPL Open Repository}, year = {2020}, url = {https://dataverse.jpl.nasa.gov/dataset.xhtml?persistentId=hdl:2014/52357} } - 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.} } - Guertin, S. M. (2018). Guideline for Single-Event Effect (SEE) Testing of System on a Chip (SOC) Devices
. NASA, 20190002148. Source
BibTeX
@techreport{guertin2018guideline, title = {Guideline for Single-Event Effect (SEE) Testing of System on a Chip (SOC) Devices}, author = {Guertin, Steven M.}, number = {20190002148}, institution = {NASA}, year = {2018}, url = {https://ntrs.nasa.gov/citations/20190002148}, abstract = {The use of complex single and multicore processors with significant cache memory, on-chip peripherals, memory controllers, and high speed input/output (IO) that integrate many of the parts of a traditional computer system is becoming more common in space applications. Such devices are often referred to as system on a chip devices (SOCs), even though the term is used somewhat inaccurately due to the lack of analog and mixed signal subcircuits. These devices are complex combinations of single- or multi-core processors with memory controllers, high-speed input/output (IO), and other peripheral structures that formerly would have been handled by off-chip resources. In the past the processors were tested for single event effects (SEE) separately, and the peripherals were often put into custom application-specific integrated circuits (ASICs) along with other resources required by the user. Performance and cost pressures have pushed commercial devices to incorporate many of the functional blocks into a single chip, an SOC. The NASA Electronic Parts and Packaging Program (NEPP) has been examining ways to perform SEE radiation hardness assurance (RHA) testing of these processor-centric SOCs to achieve reasonable understanding of their performance in space missions.} } - 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} } - 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. 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}, publisher = {JPL Open Repository}, year = {2020}, url = {https://dataverse.jpl.nasa.gov/dataset.xhtml?persistentId=hdl:2014/52311} } - Bozovich, A. and Irom, F. (2017). Compendium of Single Event Transient (SET) and Total Ionizing Dose (TID) Test Results for Commonly Used Voltage Comparators
. IEEE Radiation Effects Data Workshop. Source
BibTeX
@inproceedings{bozovich2017compendium, title = {Compendium of Single Event Transient (SET) and Total Ionizing Dose (TID) Test Results for Commonly Used Voltage Comparators}, author = {Bozovich, Amanda and Irom, Farokh}, booktitle = {IEEE Radiation Effects Data Workshop}, volume = {98}, pages = {1-21}, publisher = {IEEE}, year = {2017}, doi = {10.1109/nsrec.2017.8115430}, abstract = {This data compendium reports single event transient (SET) and total ionizing dose (TID) test results for commonly used commercial-off-the-shelf (COTS) and radiation hardened voltage comparators targeted for possible use in space-based missions. Interesting trends in the variability of the radiation performance of these devices due to differences in lot date codes, manufacturers, circuit design, and test conditions are analyzed herein.} } - Bozovich, A. N., Rax, B. G., Davila, J., Nguyen, D., Kenna, A. J., Zajac, S. A., McClure, S. S., Thomas, J. L., Scheick, L. Z., Stanford, K. W. and Gevargiz, P. (2018). Compendium of Total Ionizing Dose (TID) Test Results for the Europa Clipper Mission
. IEEE Nuclear and Space Radiation Effects Conference. Source
BibTeX
@inproceedings{bozovich2018compendium, title = {Compendium of Total Ionizing Dose (TID) Test Results for the Europa Clipper Mission}, author = {Bozovich, Amanda N. and Rax, Bernard G. and Davila, Joe and Nguyen, Duc and Kenna, Aaron J. and Zajac, Stephanie A. and McClure, Steven S. and Thomas, Jason L. and Scheick, Leif Z. and Stanford, Kelly W. and Gevargiz, Patrick}, booktitle = {IEEE Nuclear and Space Radiation Effects Conference}, pages = {1-11}, publisher = {IEEE}, year = {2018}, doi = {10.1109/nsrec.2018.8584267}, abstract = {This paper reports recent total ionizing dose (TID) test results post 300 kRad(Si) for a variety of common part types evaluated for use on NASA/JPL's Europa Clipper mission.} } - Bozovich, A. N., Nguyen, D., Rax, B. G., Davila, J. and Zajac, S. A. (2020). Investigation of Application-Specific Bias Conditions and Dose Rate Dependency in Total Ionizing Dose (TID) Response
. IEEE Radiation Effects Data Workshop. Source
BibTeX
@inproceedings{bozovich2020investigation, title = {Investigation of Application-Specific Bias Conditions and Dose Rate Dependency in Total Ionizing Dose (TID) Response}, author = {Bozovich, Amanda N. and Nguyen, Duc and Rax, Bernard G. and Davila, Joe and Zajac, Stephanie A.}, booktitle = {IEEE Radiation Effects Data Workshop}, pages = {1-6}, publisher = {IEEE}, year = {2020}, doi = {10.1109/redw51883.2020.9325830}, abstract = {This paper investigates flight circuit application bias and irradiation dose rate dependencies ("test as you fly" conditions) in the total ionizing dose (TID) response of various electronic components considered for use in a space radiation environment.} } - 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.} } - 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.} } - 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.} } - Makovsky, A., Ilott, P. and Taylor, J. (2009). Mars Science Laboratory Telecommunications System Design
. Jet Propulsion Laboratory, California Institute of Technology, Article 14. Source
BibTeX
@techreport{makovsky2009mars, title = {Mars Science Laboratory Telecommunications System Design}, author = {Makovsky, Andre and Ilott, Peter and Taylor, Jim}, series = {DESCANSO Design and Performance Summary Series}, number = {Article 14}, institution = {Jet Propulsion Laboratory, California Institute of Technology}, year = {2009}, url = {https://descanso.jpl.nasa.gov/DPSummary/Descanso14_MSL_Telecom.pdf} } - Taylor, J., Makovsky, A., Barbieri, A., Tung, R., Estabrook, P. and Thomas, A. G. (2014). Mars Exploration Rover Telecommunications
. Deep Space Communications. Source
BibTeX
@incollection{taylor2014mars, title = {Mars Exploration Rover Telecommunications}, author = {Taylor, Jim and Makovsky, Andre and Barbieri, Andrea and Tung, Ramona and Estabrook, Polly and Thomas, A. Gail}, booktitle = {Deep Space Communications}, series = {DESCANSO Design and Performance Summary Series}, publisher = {Jet Propulsion Laboratory, California Institute of Technology}, chapter = {7}, year = {2014}, url = {https://descanso.jpl.nasa.gov/monograph/series13/DeepCommo_Chapter7--141030.pdf} } - Wu, W., Wang, Q., Tang, Y., Yu, D., Wang, C., Liu, J., Zheng, L., Zhang, L. and Wang, F. (2021). Development and Prospect of Chinese Lunar Relay Communication Satellite
. Space: Science & Technology. Source
BibTeX
@article{wu2021development, title = {Development and Prospect of Chinese Lunar Relay Communication Satellite}, author = {Wu, Weiren and Wang, Qiong and Tang, Yuhua and Yu, Dengyun and Wang, Chi and Liu, Jizhong and Zheng, Lei and Zhang, Lihua and Wang, Feng}, journal = {Space: Science & Technology}, volume = {2021}, pages = {3471608}, year = {2021}, doi = {10.34133/2021/3471608}, abstract = {Relay communication satellites play a very important role on the lunar far side and pole areas exploration missions. Queqiao relay communication satellite was developed to provide relay communication support for the lander and the rover of Chang’e-4 mission landing on the far side of the Moon. From entering into the halo mission orbit around Earth-Moon libration point 2 on June 14, 2018, it has operated on the orbit more than thirty months. It worked very well and provided reliable, continuous relay communication support for the lander and the rover to accomplish the goals of Chang’e-4 lunar far side soft landing and patrol exploration mission. Exploration of the lunar south polar regions is of high scientific interest. A new relay communication satellite for Chinese south pole exploration mission is also under study. The system design and on-orbit operation status of Queqiao relay communication satellite were summarized in this paper. The system concept of the relay communication satellite for lunar south pole exploration missions is proposed. Finally, the future development and prospect of the lunar relay communication satellite system are given.} } - Towfic, Z. J., Ogbe, D., Sauvageau, J., Sheldon, D., Jongeling, A., Chien, S., Mirza, F., Dunkel, E., Swope, J., Ogut, M. and Cretu, V. (2022). Benchmarking and Testing of Qualcomm Snapdragon System-on-Chip for JPL Space Applications and Missions
. IEEE Aerospace Conference. Source
BibTeX
@inproceedings{towfic2022benchmarking, title = {Benchmarking and Testing of Qualcomm Snapdragon System-on-Chip for JPL Space Applications and Missions}, author = {Towfic, Zaid J and Ogbe, Dennis and Sauvageau, Joe and Sheldon, Douglas and Jongeling, Andre and Chien, Steve and Mirza, Faiz and Dunkel, Emily and Swope, Jason and Ogut, Mehmet and Cretu, Vlad}, booktitle = {IEEE Aerospace Conference}, pages = {1-12}, publisher = {IEEE}, year = {2022}, doi = {10.1109/aero53065.2022.9843518}, abstract = {As some space missions become more challenging due to new environments, greater distances, or more limited size, weight, and power (SWaP) constraints, spacecraft avionics must adapt to allow the spacecraft to be more autonomous and agile‐‐‐eliminating the Spacecraft-Earth-Spacecraft feedback loop whenever possible. Prime examples of such missions include Aerobots (such as Ingenuity with extremely low SWaP constraints and demanding signal/image processing during flight) and landers in possibly hostile environments (such as a Europa lander mission, with limited communication capacity, high latency, and constrained power budget). To address these challenges, JPL worked with Qualcomm to demonstrate the use of their Snapdragon 801 system-on-chip (SoC) onboard the Ingenuity Helicopter on Mars. The Qualcomm Snapdragon SoC contains various subsystems, including an ARM cluster, a Graphics processing unit, a Digital Signal Processing subsystem, a Neural Processing Engine, Image Signal Processing subsystem, among others. Since the success of Ingenuity, JPL is continuing to work with Qualcomm to address other applications of the Snapdragon SoC technology. This includes the deployment of two 855 Snapdragon development boards onboard the International Space Station (ISS) for successful in-situ benchmarking of applications in space (beyond those tested on Ingenuity). In this paper, we will examine the performance of various applications that have been identified to benefit from greater onboard computational capability. These applications include (among others): machine vision algorithms that are expected to be critical in autonomous entry-descent-and-landing scenarios and real-time Aerobot flight navigation; Hyperspectral compression algorithms; Synthetic Aperture Radar Processing along with various instrument processing algorithms. We discuss how the infusion of Qualcomm's Snapdragon SoC is capable of enabling missions that may not have been able to achieve their goals with traditional flight computing. In addition, we also show that for some algorithms, the software implementation on the Snapdragon SoC outperforms traditional FPGA implementations.} } - Villalpando, C. Y., Morfopoulos, A., Matthies, L. and Goldberg, S. (2011). FPGA Implementation of Stereo Disparity with High Throughput for Mobility Applications
. IEEE Aerospace Conference. Source
BibTeX
@inproceedings{villalpando2011fpga, title = {FPGA Implementation of Stereo Disparity with High Throughput for Mobility Applications}, author = {Villalpando, Carlos Y. and Morfopoulos, Arin and Matthies, Larry and Goldberg, Steven}, booktitle = {IEEE Aerospace Conference}, pages = {1--11}, address = {Big Sky, Montana}, year = {2011}, doi = {10.1109/aero.2011.5747269}, abstract = {High speed stereo vision can allow unmanned robotic systems to navigate safely in unstructured terrain, but the computational cost can exceed the capacity of typical embedded CPUs. In this paper, we describe an end-to-end stereo computation co-processing system optimized for fast throughput that has been implemented on a single Virtex 4 LX160 FPGA. This system is capable of operating on images from a 1024 × 768 3CCD (true RGB) camera pair at 15 Hz. Data enters the FPGA directly from the cameras via Camera Link and is rectified, pre-filtered and converted into a disparity image all within the FPGA, incurring no CPU load. Once complete, a rectified image and the final disparity image are read out over the PCI bus, for a bandwidth cost of 68 MB/sec. Within the FPGA there are 4 distinct algorithms: Camera Link capture, Bilinear rectification, Bilateral subtraction pre-filtering and the Sum of Absolute Difference (SAD) disparity. Each module will be described in brief along with the data flow and control logic for the system. The system has been successfully fielded upon the Carnegie Mellon University's National Robotics Engineering Center (NREC) Crusher system during extensive field trials in 2007 and 2008 and is being implemented for other surface mobility systems at JPL.} } - Jones, C. S. J. and Nola, F. J. (1971). Mobility systems activity for lunar rovers at MSFC
. NASA, NASA-TM-. Source
BibTeX
@techreport{jones1971mobility, title = {Mobility systems activity for lunar rovers at MSFC}, author = {Jones, C. S., Jr. and Nola, F. J.}, number = {NASA-TM-}, institution = {NASA}, year = {1971}, url = {https://ntrs.nasa.gov/citations/19720004516}, abstract = {The Apollo Lunar Roving Vehicle (LRV) mobility system is described. Special emphasis is given to the redundancy aspects and to the selection of the drive motors. A summary chart of the performance on the lunar surface during the Apollo 15 flight is included. An appendix gives details on some development work on high efficiency drive systems and compares these systems to the selected system.} } - Chun, W. and Brunson, P. (1987). Actuators for a Space Manipulator
. NASA, 19890000730. Source
BibTeX
@techreport{chun1987actuators, title = {Actuators for a Space Manipulator}, author = {Chun, W. and Brunson, P.}, number = {19890000730}, institution = {NASA}, year = {1987}, url = {https://ntrs.nasa.gov/citations/19890000730}, abstract = {The robotic manipulator can be decomposed into distinct subsytems. One particular area of interest of mechanical subsystems is electromechanical actuators (or drives). A drive is defined as a motor with an appropriate transmission. An overview is given of existing, as well as state-of-the-art drive systems. The scope is limited to space applications. A design philosophy and adequate requirements are the initial steps in designing a space-qualified actuator. The focus is on the d-c motor in conjunction with several types of transmissions (harmonic, tendon, traction, and gear systems). The various transmissions will be evaluated and key performance parameters will be addressed in detail. Included in the assessment is a shuttle RMS joint and a MSFC drive of the Prototype Manipulator Arm. Compound joints are also investigated. Space imposes a set of requirements for designing a high-performance drive assembly. Its inaccessibility and cryogenic conditions warrant special considerations. Some guidelines concerning these conditions are present. The goal is to gain a better understanding in designing a space actuator.} } - Dursch, H. W., Spear, W. S., Miller, E. A., Bohnhoff-Hlavacek, G. L. and Edelman, J. (1992). Analysis of systems hardware flown on LDEF. Results of the systems special investigation group
. Legacy CDMS, 19920022433. Source
BibTeX
@techreport{dursch1992analysis, title = {Analysis of systems hardware flown on LDEF. Results of the systems special investigation group}, author = {Dursch, Harry W. and Spear, W. Steve and Miller, Emmett A. and Bohnhoff-Hlavacek, Gail L. and Edelman, Joel}, number = {19920022433}, institution = {Legacy CDMS}, year = {1992}, url = {https://ntrs.nasa.gov/citations/19920022433}, abstract = {The Long Duration Exposure Facility (LDEF) was retrieved after spending 69 months in low Earth orbit (LEO). LDEF carried a remarkable variety of mechanical, electrical, thermal, and optical systems, subsystems, and components. The Systems Special Investigation Group (Systems SIG) was formed to investigate the effects of the long duration exposure to LEO on systems related hardware and to coordinate and collate all systems analysis of LDEF hardware. Discussed here is the status of the LDEF Systems SIG investigation through the end of 1991.} } - Miller, D. L. (2015). Development of Resource-Constrained Sensors and Actuators for In-Space Satellite Docking and Servicing. Source
BibTeX
@mastersthesis{miller2015development, title = {Development of Resource-Constrained Sensors and Actuators for In-Space Satellite Docking and Servicing}, author = {Miller, Duncan L.}, school = {Massachusetts Institute of Technology}, type = {S.M. thesis}, year = {2015}, url = {https://dspace.mit.edu/handle/1721.1/98805} } - Gaier, J. R. (2005). The Effects of Lunar Dust on EVA Systems During the Apollo Missions
. NASA Glenn Research Center, NASA/TM-2005-213610, 20050160460. Source
BibTeX
@techreport{gaier2005effects, title = {The Effects of Lunar Dust on EVA Systems During the Apollo Missions}, author = {Gaier, James R.}, number = {NASA/TM-2005-213610, 20050160460}, institution = {NASA Glenn Research Center}, year = {2005}, url = {https://ntrs.nasa.gov/citations/20050160460}, abstract = {Mission documents from the six Apollo missions that landed on the lunar surface have been studied in order to catalog the effects of lunar dust on Extra-Vehicular Activity (EVA) systems, primarily the Apollo surface space suit. It was found that the effects could be sorted into nine categories: vision obscuration, false instrument readings, dust coating and contamination, loss of traction, clogging of mechanisms, abrasion, thermal control problems, seal failures, and inhalation and irritation. Although simple dust mitigation measures were sufficient to mitigate some of the problems (i.e., loss of traction) it was found that these measures were ineffective to mitigate many of the more serious problems (i.e., clogging, abrasion, diminished heat rejection). The severity of the dust problems were consistently underestimated by ground tests, indicating a need to develop better simulation facilities and procedures.} }