Lockheed Martin Space Systems Company Research Articles

The Use of Low Temperature Lithium-Ion Batteries to Enable the NASA Insight Mission on Mars

On November 26, 2018, the NASA InSight spacecraft successfully landed on the surface of Mars, with the intent of investigating the interior structure of the planet. The Mars InSight mission, which is an acronym for “Interior Exploration using Seismic Investigations, Geodesy and Heat Transport”, consists of a single lander performing geophysical measurements and studying its deep interior.1,2 The spacecraft, which was built by Lockheed Martin Space Systems Company, is based upon a design that was successfully used for NASA’s 2007 Phoenix Mars lander. However, unlike the previous lander and rover missions to Mars, the InSight mission required a higher specific energy battery that can operate over a wider temperature range, with both charging and discharging from -30oC to +35oC. To meet these challenging mission requirements, the project adopted the use of the next generation Li-ion chemistry, which consists of graphite-LiNiCoAlO2 (NCA), coupled with a JPL developed low temperature electrolyte comprised of 1.0M LiPF6 in ethylene carbonate (EC) + ethyl methyl carbonate (EMC) + methyl propionate (MP) (20:60:20 vol%)3-7. This advanced Li-ion chemistry, which was manufactured by Eagle Picher-Yardney Division, has proven to be mission enabling and has displayed good performance over a wide temperature range, including excellent storage and cycle life characteristics. To meet the primary mission requirements, the battery must support a calendar life of four years and operation on the surface of Mars for 709 sols (a duration of over one Martian year). As noted above, one of the more challenging mission requirements is the ability to both charge and discharge the battery at very low temperatures (-30oC) using moderately aggressive rates (i.e., C/5 rates based on the nameplate capacity of 25Ah). In addition to having to support the power and energy requirements under these conditions, there was some concern that lithium plating on the anode could occur during the low temperature charging which may lead to performance degradation.8 Furthermore, there was some concern that the low temperature capability of the battery could be compromised by being subjected to long, high temperature operation, making end of mission requirements difficult to meet. To address these concerns, a comprehensive performance test program was under-taken, which included the following: (i) determining the impact of high temperature exposure, (ii) simulating the launch pad storage conditions, (iii) continuously cycling between the temperature extremes (+30oC, +20oC, -25oC, and -30oC) with periodic diagnostic capacity and impedance characterization at +30oC, -25oC and -30oC, (iv) low temperature charge and discharge characterization (-25oC to -40oC), and (v) accelerated mission relevant testing, consisting of 60% DOD cycling over a wide temperature range. In summary, the InSight Li-Ion chemistry with an ester-containing low temperature electrolyte delivered improved performance compared to the compared to the heritage NCO-based chemistry which has been used on previous rover and lander missions to Mars, including: (i) >15% higher capacity and energy at ambient temperature, (ii) superior low temperature performance (-25oC and below), and (iii) improved resilience to high temperature exposure. Furthermore, the battery chemistry was demonstrated to be very resilient to continuous operation at -30oC, with no indirect evidence of lithium plating occurring or noticeable performance degradation observed. Thus far, the flight batteries have completed over 100 Sols of operation of the surface of Mars and have displayed excellent performance and health characteristics. ACKNOWLEDGEMENT The work described here was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under contract with the National Aeronautics and Space Administration (NASA) and supported by the Mars InSight Mission. M. Golombek, et al., “Selection of the InSight Landing Site”, Space Sci. Rev., 211, 5-95 (2017). M. E. Lisano and P. H. Kallemeyn, 2017 IEEE Aerospace Conference, 1-11 (2017). M. C. Smart, and B. V. Ratnakumar, L. D. Whitcanack, K. A. Smith, S. Santee, R. Gitzendanner, V. Yevoli, ECS Trans., 11, (29) 99 (2008). M. C. Smart, B. V. Ratnakumar, K. B. Chin, and L. D. Whitcanack, J. Electrochem. Soc., 157 (12), A1361-A1374 (2010). M. C. Smart, S. F. Dawson, R. B. Shaw, L. D. Whitcanack, A. Buonanno, C. Deroy, and R. Gitzendanner, “Performance Validation of Yardney Low Temperature NCA-Based Li-ion Cells for the NASA Mars InSight Mission”, NASA Aerospace Battery Workshop, Huntsville, Alabama, November 18-20, 2014. M. C. Smart, and R. V. Bugga, U. S. Patent 8,920,981. (December 20, 2014). M. C. Smart, B. V. Ratnakumar, R. C. Ewell, S. Surampudi, F. Puglia, and R. Gitzendanner, “The Use of Lithium-Ion Batteries for JPL’s Mars Missions”, Electrochimica Acta, 268, 27-40 (2018) M. C. Smart and B. V. Ratnakumar, J. Electrochem. Soc., 158 (4), A379-A389 (2011).

The Use of Ester Co-Solvent Based Low Temperature Electrolytes in Experimental and Large Capacity Prototype Graphite-LiNiCoAlO2 Lithium-Ion Cells

The 2003 Mars Exploration Rover (MER) and the Mars Science Laboratory (MSL) Curiosity Rover utilize a large capacity rechargeable Li-ion batteries that have been manufactured by EaglePicher-Yardney Division (Yardney). The cell chemistry adopted for these missions consists of mesocarbon microbeads (MCMB) anodes, LiNixCo1-xO2 cathode materials, and a low temperature ternary all-carbonate-based electrolyte developed at JPL1,2,3 encased in a hermetically sealed prismatic can. The attractiveness of this system is that it displays long life, high specific energy and the ability to operate over a wide temperature range, including charging and discharging at -20oC. Due to favorable performance characteristics and the heritage established, this cell chemistry has been used on other NASA missions, including the 2007 Phoenix Lander, Grail, and the current Juno mission to Jupiter. To meet even more challenging performance requirements, including the ability to be charged and discharged at -30oC, the Mars InSight lander, which is a spacecraft being built by Lockheed Martin Space Systems Company, will utilize the next generation LiNiCoAlO2 (NCA)-based chemistry, which incorporates a JPL developed ester containing low temperature electrolyte. 4,5,6 In the context of supporting possible future missions to the distant icy moons of Jupiter and Saturn, we are currently evaluating the potential of this system to operate at very low temperatures.7 To enable the exploration of the surfaces of these icy moons, one will require power systems that can potentially operate at ultra-low temperatures (down to -180oC) in high radiation environments. To meet these challenging requirements, we are currently developing ultra-low temperature rechargeable batteries with high specific energy and long life and with the ability to operate over the temperature range of +40oC to -60oC. It is preferred that the cells are capable of continuous operation at very low temperatures, so an emphasis has been focused upon demonstrating efficient charge characteristics over a wide temperature range. In this context, we have investigated a number of electrolytes that contain methyl propionate (MP) as a co-solvent, as well as various additives, to determine their influence upon the low temperature capacity (i.e., down to -65oC). In addition to evaluating the charge and discharge characteristics over a wide temperature range in large capacity prismatic cells and prototype pouch cells, experimental graphite - LiNiCoAlO2 three-electrode lithium-ion cells were used to determine the influence of electrolyte type upon the electrode kinetics over a range of temperatures. ACKNOWLEDGEMENT The work described here was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under contract with the National Aeronautics and Space Administration (NASA) and supported by the Ocean Worlds Program Office. REFERENCES 1. M.C. Smart, B.V. Ratnakumar, and S. Surampudi, “Electrolytes for Low Temperature Lithium-Ion Batteries Based on Mixtures of Aliphatic Carbonates”, J. Electrochem.Soc., 146, 486 (1999). 2. M. C. Smart, B. V. Ratnakumar, L. Whitcanack, S. Surampudi, J. Byers, and R. Marsh, IEEE Aerospace and Electronic Systems Magazine, 14: 11, 36-42 (1999). 3. M. C. Smart, B. V. Ratnakumar, L. D. Whitcanack, K. B. Chin, S. Surampudi, R. Gitzendanner, F. J. Puglia, and J. Byers, “Lithium-ion Batteries for Aerospace”, IEEE Aerospace and Electronic Systems Magazine, 19:1, 2004, pp. 18-25. 4. M.C. Smart, and B.V. Ratnakumar, L.D. Whitcanack, K.A. Smith, S. Santee, R. Gitzendanner, V. Yevoli, “Li-Ion Electrolytes Containing Ester Co-Solvents for Wide Operating Temperature Range”, ECS Trans. 11, (29) 99 (2008). 5. M. C. Smart, B. V. Ratnakumar, K. B. Chin, and L. D. Whitcanack, “Lithium-Ion Electrolytes Containing Ester Co-solvents for Improved Low Temperature Performance”, J. Electrochem. Soc., 157 (12), A1361-A1374 (2010). 6. M. C. Smart, S. F. Dawson, R. B. Shaw, L. D. Whitcanack, A. Buonanno, C. Deroy, and R. Gitzendanner, “Performance Validation of Yardney Low Temperature NCA-Based Li-ion Cells for the NASA Mars InSight Mission”, NASA Aerospace Battery Workshop, Huntsville, Alabama, November 18-20, 2014. 7. M. C. Smart, F. C. Krause, J. –P. Jones, L. D. Whitcanack, B. V. Ratnakumar, and E. J. Brandon, “The Use of Low Temperature Electrolytes in High Specific Energy Li-Ion Cells for Future NASA Missions to Icy Moons”, 229th Meeting of the Electrochemical Society, San Diego, May 29-June 2, 2016.

Field-Reversible Thermal Connector (RevCon) Challenges: A Review

Thermal connectors (card holder, retainer, thermal connector, etc.) have played a critical thermal management role for decades for electronic components. The Defense Advanced Research Projects Agency (DARPA) and the Office of Naval Research have long been aware of the importance of this thermal management technology, and as such hosted the first two Field-Reversible Thermal Connector (RevCon) challenges. Later, with DARPA’s support, the University of Missouri hosted the RevCon III and RevCon IV competitions in 2014 and 2015. The number of competing teams has increased from four in RevCon I to nine in the first phase of RevCon III and 11 in RevCon IV. This event has expanded by creating: 1) crowdsourcing with more effective channels; 2) broader involvement from international teams; 3) an effective two-phase down-selecting procedure so that the uniqueness of their concept, concept feasibility, mass production cost analysis, complete project plan, and the delivery of a real prototype after the execution of the first phase can be well evaluated; and 4) better judgment on thermal performance with the combination of vibration and vacuum testing by experts from AFRL, Rockwell Collins, Honeywell, Raytheon Integrated Defense Systems, BAE Systems, HRL, Lockheed Martin Space Systems Company, and Advanced Cooling Technologies Corporation. Progressively challenging metrics were set for participating teams to achieve in subsequent challenges, leading to unique and novel prototype concepts from the teams. The thermal performance of the prototypes is generally outstanding: the majority outperforming advanced commercial-off-the shelf thermal connectors with thermal resistance values as low as 0.1 °C/W.

MatlSSE Microcryocooler

Lockheed Martin Space Systems Company has built and delivered an engineering model microcryocooler to the Jet Propulsion Laboratory for use with instruments for deep space and earth science missions. Funding for this cryocooler was through JPL's Maturation of Instruments for Solar System Exploration (MatISSE). This cooler is nearly identical to the compact coaxial microcryocooler presented at the 2014 International Cryocooler Conference. The cryocooler mass is just 345 grams for the entire thermal mechanical unit, and is compact enough to be packaged in a CubeSat. This paper describes the measured performance of the MatISSE cryocooler, including the performance at cold heat rejection temperatures.

Employment opportunities at Lockheed Martin Space Systems company (LMSSC)

Employment opportunities at Lockheed Martin Space Systems company (LMSSC)

The Goldilocks Theory

The Goldilocks Theory

Lockheed Martin Space Systems Company Optimizes Infrastructure Project-Portfolio Selection

Lockheed Martin Space Systems Company spends millions of dollars on the maintenance and modernization of its infrastructure each year. Projects often involve investments that cannot be justified purely in terms of net present value or other classical investment-evaluation methods. The options are also restricted because funds that are not spent within a given time frame must be relinquished. Furthermore, some projects may be delayed and the unplanned carryover of their costs moved into the next fiscal year; this causes the postponement or cancellation of other unrelated projects because of in-budget transfers. In this paper, we used multiattribute utility theory and chance-constrained programming to optimize the selection of infrastructure projects. Our solution ensured the selection of high-value projects to maximize the company's performance. These selections were subject to the constraints that a portfolio did not exceed the available budget and that the carryover of the unspent funds to the next fiscal year did not exceed predetermined limits. We used Microsoft Excel to ensure broad accessibility, transparency, user interaction, improved data collection and asset management, and ease-of-use by managers.

Planning, implementation and optimization of future space missions using an immersive visualization environment (IVE) machine

Beginning in 1995, a team of 3-D engineering visualization experts assembled at the Lockheed Martin Space Systems Company and began to develop innovative virtual prototyping simulation tools for performing ground processing and real-time visualization of design and planning of aerospace missions. At the University of Colorado, a team of 3-D visualization experts also began developing the science of 3-D visualization and immersive visualization at the newly founded British Petroleum (BP) Center for visualization, which began operations in October, 2001. BP acquired ARCO in the year 2000 and awarded the 3-D flexible IVE developed by ARCO (beginning in 1990) to the University of Colorado, CU, the winner in a competition among 6 Universities. CU then hired Dr. G. Dorn, the leader of the ARCO team as Center Director, and the other experts to apply 3-D immersive visualization to aerospace and to other University Research fields, while continuing research on surface interpretation of seismic data and 3-D volumes. This paper recounts further progress and outlines plans in Aerospace applications at Lockheed Martin and CU.

19th Aerospace mechanisms symposium

The Aerospace Mechanisms Symposium (AMS) provides a unique forum for those active in the design, production and use of aerospace mechanisms. A major focus is the reporting of problems and solutions associated with the development and flight certification of new mechanisms. The National Aeronautics and Space Administration and Lockheed Martin Space Systems Company (LMSSC) share the responsibility for organizing the AMS. Now in its 34th year, the AMS continues to be well attended, attracting participants from both the U.S. and abroad. The 34th AMS, hosted by the Goddard Space Flight Center (GSFC) in Greenbelt, Maryland, was held May 10, 11 and 12, 2000. During these three days, 34 papers were presented. Topics included deployment mechanisms, bearings, actuators, pointing and optical mechanisms, Space Station mechanisms, release mechanisms, and test equipment. Hardware displays during the vendor fair gave attendees an opportunity to meet with developers of current and future mechanism components.