Theory and Application of the Power Tools Suite (PTS) for General Orbital EPS Applications

Bailey, P.G.; Gibbs, C.; Hollandsworth, R.P.; Armantrout, Jon; Martin, Lockheed

doi:10.2514/6.2005-5612

Cited by 4 publications

(4 citation statements)

References 2 publications

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“…Descriptions of the development of this PTS code and its results have been presented at several IECEC and Space Power Workshop conferences in recent years. [1][2][3][4][5][6][7][8][9][10] The Power Tools Suite codes package originated in the late 1990s for use in the Iridium Program and in other specific programs within Lockheed Martin. [11][12][13] The Models and Codes have been significantly updated several times during the past few years and have been displayed at a recent Lockheed Martin Corporate joint Space Systems Company and Advanced Technology Center modeling and simulations conference.…”

Section: The Updated Power Tools Suite (Pts) Codementioning

confidence: 99%

“…The PTS Dynamic Code contains all of the EPS Component Models and the ability to connect the models in any EPS configuration. [5][6] The numerical solution algorithm has been carefully written to provide numerical convergence on the voltage and current values within the EPS for any conditions: temperatures, solar array input parameters (e.g. light intensity, insolation or insol, angle), battery conditions (e.g.…”

Section: The Updated Power Tools Suite (Pts) Codementioning

confidence: 99%

“…constant power or constant current). 7 The PTS Dynamic Code currently contains 930 various subroutines and function, over 20 different battery cell models, and over 83,000 lines of code.…”

Section: The Updated Power Tools Suite (Pts) Codementioning

confidence: 99%

“…Additional information on the various PTS EPS component models, and the EPS bus designs that have been modeled, can be found in previously released IECEC and Space Power Workshop papers. [1][2][3][4][5][6][7][8][9][10]…”

Section: The Updated Power Tools Suite (Pts) Codementioning

confidence: 99%

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The Adverse Effects of Not Including Capacity Addition During LiIon Taper Charging in EPS Sizing for LEO Missions

Bailey¹,

Martin²

2011

9th Annual International Energy Conversion Engineering Conference

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In the design of the Electrical Power System, the batteries are used during the eclipse cycle where there is no sunlight, to provide energy to a certain depth-of-discharge (DOD), and are charged during the times that the spacecraft is in the sun. For high orbits, such as Geosynchronous Earth Orbit (GEO), there is ample time to charge both Nickel Hydrogen (NiH) and Lithium Ion (LiIon) battery cells from the maximum allowed DOD back to a full condition. For Low Earth Orbit (LEO) satellites with high energy use profiles, charging current restrictions may limit the amount of current available for charging per orbit, and full recharging may not occur until after a certain number or many complete orbits. This paper discusses the advantages and limitations of allowing or disallowing the including of the capacity addition during the taper charging portion of the recharging cycle for LiIon battery cells. Taper charging is defined to begin when the maximum specified charging voltage is reached, and may continue until the cell is fully charged. Some researchers have suggested that the capacity addition during taper charging might not be allowed in order to offset other capacity losses that may occur, such as during cell rebalancing.

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Section: The Updated Power Tools Suite (Pts) Codementioning

confidence: 99%

Section: The Updated Power Tools Suite (Pts) Codementioning

confidence: 99%

“…constant power or constant current). 7 The PTS Dynamic Code currently contains 930 various subroutines and function, over 20 different battery cell models, and over 83,000 lines of code.…”

Section: The Updated Power Tools Suite (Pts) Codementioning

confidence: 99%

Section: The Updated Power Tools Suite (Pts) Codementioning

confidence: 99%

See 2 more Smart Citations

The Adverse Effects of Not Including Capacity Addition During LiIon Taper Charging in EPS Sizing for LEO Missions

Bailey¹,

Martin²

2011

9th Annual International Energy Conversion Engineering Conference

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Advanced Battery Models from Test Data for Specific Satellite EPS Applications

Bailey

Hollandsworth

Armantrout

2006

4th International Energy Conversion Engineering Conference and Exhibit (IECEC)

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Detailed battery models are required for accurate Electric Power System (EPS) simulations of satellites in various LEO, MEO, and GEO missions. Older and outdated models had used various power margins to over-estimate the size and weight of the satellite EPS for a given mission. Today's models incorporate the use of databases of battery test data from various testing facilities to much better and more accurately predict past, current, and future mission battery behavior. This paper describes various battery types, cell types, a database of data that have been collected and analyzed, and overviews the detailed models that have been developed for applications from that data. The battery models include Nickel Hydrogen, Lithium Ion, and Nickel Cadmium battery cells. Independent variables for these models include capacity, number of cells, charging and discharging, charge and discharge rates, temperature, and battery cell age. Model options also include cell dropouts vs. time, and variable sensitivity analyses. These models have been benchmarked to their corresponding data, and have been implemented into various simulation studies for various missions, such as for the Hubble Space Telescope battery depletion problem. The use of these models provides much more accurate simulations of EPS behavior, battery degradation, and lifetime estimates that are needed in the Aerospace Industry today.

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EPS Sensitivity Studies Using the PTS Simulation Code for Specific Satellite Applications

Bailey

Armantrout

2008

6th International Energy Conversion Engineering Conference (IECEC)

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Theory and Application of the Power Tools Suite (PTS) for General Orbital EPS Applications

Cited by 4 publications

References 2 publications

The Adverse Effects of Not Including Capacity Addition During LiIon Taper Charging in EPS Sizing for LEO Missions

The Adverse Effects of Not Including Capacity Addition During LiIon Taper Charging in EPS Sizing for LEO Missions

Advanced Battery Models from Test Data for Specific Satellite EPS Applications

EPS Sensitivity Studies Using the PTS Simulation Code for Specific Satellite Applications

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