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.
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
. Earth and Space, 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 = {Earth and Space}, 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} }