Reconciling Scientific Aspirations and Engineering

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Recent work at JPL seeks to enhance communication between these two ... mission is conducted with two 2-astronaut teams, each of which drives a pressurized ...

AIAA 2010-8880

AIAA SPACE 2010 Conference & Exposition 30 August - 2 September 2010, Anaheim, California

Reconciling Scientific Aspirations and Engineering Constraints for a Lunar Mission via Hyperdimensional Interpolation

Downloaded by NASA GODDARD SPACE FLIGHT CENTER on December 19, 2015 | http://arc.aiaa.org | DOI: 10.2514/6.2010-8880

Charles R. Weisbin 1, Alberto Elfes, Jeffrey H. Smith, Joseph Mrozinski, Virgil Adumitroaie, Hook Hua, Kacie Shelton, William Lincoln, Robert Silberg Jet Propulsion Laboratory, California Institute of Technology, 4800 Oak Grove Drive, Pasadena, CA 91109 and Pamela Clark, Mark Lupisella Goddard Space Flight Center, 8800 Greenbelt Road, Greenbelt, Maryland 20771

With the goal of facilitating communication and cooperation between NASA’s scientific and engineering/design communities, a tool (in the form of a table) is developed which displays the majority of the architectural-parameter trade space under consideration for a given mission, enabling all interested parties to see which sets of constraints would be acceptable for a desired level of science or any other objective. A combination of computer optimization runs and interpolation is employed to enable calculation of the table within a reasonable period of time. Three alternative interpolation methods (radial basis function (RBF), kriging, and regression) are investigated. A hypothetical mission to the Moon’s Schrödinger crater serves as a test case. Kriging, with the lowest average error rate, is judged to be the best interpolation method for this case study, but the more consistent results of the regression method may be preferable in certain other circumstances.

Nomenclature EVA IVA

V

= Extravehicular activity (i.e., outside a pressurized cabin, requiring a space suit) = Intravehicular activity (i.e., inside a pressurized cabin, not requiring a space suit)

I. Introduction

IRTUALLY every NASA space-exploration mission represents a compromise between the interests of two expert, dedicated, but very different communities: scientists, who want to go quickly to the places that interest them most and spend as much time there as possible conducting sophisticated experiments, and the engineers and designers charged with maximizing the probability that a given mission will be successful (astronauts kept safe and objectives achieved) and cost-effective. Recent work at JPL seeks to enhance communication between these two groups, and to help them reconcile their interests, by developing advanced modeling capabilities with which they can analyze the achievement of science goals and objectives against engineering design and operational constraints.

II. Analysis 1

Our analyses conducted prior to this study have been point-design driven. Each analysis has been of one hypothetical case which addresses the question: Given a set of constraints, how much science can be done? But the constraints imposed by the architecture team—e.g., rover speed, time allowed for extravehicular activity (EVA), number of sites at which science experiments are to be conducted—are all in early development and carry a great deal of uncertainty. Variations can be incorporated into the analysis, and indeed that has been done in sensitivity studies designed to see which constraint variations have the greatest impact on results. 1

Deputy Program Manager, System Modeling and Analysis Program Office; [email protected] 1 American Institute of Aeronautics and Astronautics

Copyright © 2010 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

Downloaded by NASA GODDARD SPACE FLIGHT CENTER on December 19, 2015 | http://arc.aiaa.org | DOI: 10.2514/6.2010-8880

But if a very large number of variations can be analyzed all at once, producing a table that includes the majority of the trade space under consideration, then we have a tool that enables scientists and mission architects to ask the inverse question: For a given desired level of science (or any other objective), what are the sets of constraints that would be acceptable? (Note that the solution is not unique.) With this tool, mission architects could determine, for example, what combinations of rover speed, EVA duration, and other constraints produce the desired results. Further, this tool would help them identify which technology-improvement investments would be likely to produce the largest or most important return. However, the number of variations that need to be considered for such analysis quickly balloons to an unwieldy size. If three variations are considered for each of five constraints—a very modest example—there are a total of 243 (3 to the 5th power) variations to consider. If it takes 40 minutes to compute each variation (as when our automated optimization system, HURON2, computes the complicated mission analysis described below), a full analysis consisting solely of computer runs would take 162 hours or nearly 7 days of round-the-clock computing to calculate the results. Adding further constraints or variations exponentially increases the amount of time that is needed. In this study, we explore three methods—radial basis function (RBF), kriging, and regression—for interpolating the bulk of the trade space based on actual computations of less than 20% of the space, which dramatically reduces the time needed to compute results over the full trade space. RBF is found to carry a higher error rate than the other two and to be the least suitable for our purposes. Choosing between kriging and regression, however, is more complicated. Depending on the intended use, one might choose kriging (as we did) for its lower average error rate or regression for its more consistent—albeit somewhat higher—error rate. A. Baseline Study The subject of our study is a hypothetical mission to Schrödinger crater, which is thought to expose underlying stratigraphic material from South Pole Aitken Basin, the oldest, largest basin on the Moon. The allotted round-trip time from an assumed base camp at Shackleton crater to Schrödinger and back is 90 days. Figure 1 lays out the geometry of the mission in the baseline study. Blue dots indicate primary (required) localities for science experiments, while orange dots indicate secondary (optional) localities where scientific experiments would enhance mission results. Each of these localities comprises 6 sites Figure 1. Geometry of a hypothetical 90-day excursion from an outpost at where scientific activities Shackleton crater (lower right) to Schrödinger crater and back. are to be performed. The mission is conducted with two 2-astronaut teams, each of which drives a pressurized rover that is periodically recharged by a separate, slower vehicle operated remotely from Earth. A target list of experiments and other activities is derived from the scientific objectives expressed by sources such as the National Research Council, the Global Exploration Strategy, and the Lunar Exploration Analysis Group3. Each experiment and activity is assigned a relative science value and a cost in terms of EVA time required. A set of constraints is provided by a missionarchitecture team as follows: 1. maximum EVA time per day 2. maximum EVA time per locality 2 American Institute of Aeronautics and Astronautics

rover speed number of localities included (3 combinations of primary and secondary localities are considered: 5 primary + 14 secondary totaling 19; 10 primary + 28 secondary totaling 38; and 15 primary + 36 secondary totaling 51) 5. time needed for egress from and ingress into the rover’s pressurized cabin A baseline solution of the Schrödinger excursion problem is computed, using HURON. It is found that the 90 days allowed for the mission provide ample time to conduct the desired activities at all primary sites and many secondary sites. Given these conditions, the constraint on EVA time, during which all scientific activities are conducted, is found to be the primary driver of results. A significant amount of IVA time (i.e., intravehicular activity time, when the astronauts are inside the pressurized cabins of their rovers) is included in the mission profile, during which further science activities could potentially be conducted if that were permitted and enabled. Downloaded by NASA GODDARD SPACE FLIGHT CENTER on December 19, 2015 | http://arc.aiaa.org | DOI: 10.2514/6.2010-8880

3. 4.

B. Response Surface Analysis In the next phase of the study, the objective is to determine the ranges for a variety of architecture parameters that achieve equivalent levels of science return. With 3 variables for each of 5 constraints, the trade space is an irregular, multidimensional (aka hyperdimensional) grid. Forty-two cases are run on HURON, and the remaining 83% of cases are interpolated using each of the three methods stated above. The analysis produces results for 5 parameters: productivity, cost, mission duration, kilometers traversed, and percentage of targeted experiments conducted (in which each experiment is weighted by the importance assigned by scientists participating in the study). We choose to sort the results by this percentage, but the sorting could just as easily be done by any or all of the other parameters. Results are validated and an error rate is computed for each interpolation method (Fig. 2).

Figure 2. Comparison of the error rates of 3 interpolation methods. Kriging (the purple curve) is found to have the lowest average error rate and is used to compute a table in which the 243 cases are ranked by the percentage described above (Table 1). The rows near the top of the table thus represent the cases that would likely be selected by mission architects who wish to maximize the return from experiments conducted during this mission. Given this information, they would be able to further winnow the choices according to other constraints that are not included in this analysis—e.g., public outreach considerations or participation by other countries.

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Table 1. The product of the response surface analysis.

Sections are shown from the top, middle and bottom of the table, which consists of 243 cases. The orange-headed columns are the 5 constraints discussed above. The blue-headed column gives the number by which the cases are ranked: the percentage of targeted experiments that are conducted, in which each experiment is weighted by the importance assigned by scientists participating in the study.

III. Conclusion We have shown that we can survey a very broad range of combinations of architect parameters through a combination of computer optimization runs and interpolation, and that we can provide an estimate of the quality of the results by a number of different methods. Increasing the number of computer runs decreases the interpolation error rate. Of the three interpolation methods employed in this study, kriging (which had the lowest average error 4 American Institute of Aeronautics and Astronautics

rate) was found to be best for our purposes, but the more consistent results of the regression method (the yellow curve in Figure 2) may be preferable in certain circumstances.

Acknowledgments

Downloaded by NASA GODDARD SPACE FLIGHT CENTER on December 19, 2015 | http://arc.aiaa.org | DOI: 10.2514/6.2010-8880

The authors gratefully acknowledge the support and encouragement of Doug Craig of the Exploration Systems Mission Directorate Integration Office (DIO). Pat Troutman, Daniel Mazanek, David Reeves, and Julie Williams Byrd of LaRC, supporting the DIO, provided guidance and feedback from the Architect Team, and Ruthan Lewis provided guidance and feedback from the Optimizing Science and Exploration Working Group support team. The research described in this paper was performed at the Jet Propulsion Laboratory (JPL), California Institute of Technology, under a contract with the National Aeronautics and Space Administration

References 1

Weisbin, C. R., J. Mrozinski, W. Lincoln, A. Elfes, K. Shelton, H. Hua, J. H. Smith, V. Adumitroaie, R. Silberg, "Lunar Architecture and Technology Analysis Driven by Lunar Science Scenarios," Systems Engineering Journal, Vol. 13, Number 3, 2010. 2 Elfes, A., C. R. Weisbin, H. Hua, J. H. Smith, J. Mrozinski, and K. Shelton, “The HURON Task Allocation and Scheduling System: Planning Human and Robot Activities for Lunar Missions,” Proceedings of the WAC 2008 International Symposium on Intelligent Automation and Control (ISIAC 2008), Waikoloa, Hawaii, September 2008. 3 CAPTEM-LEAG, “CAPTEM-LEAG analysis document: Review of sample acquisition and curation during lunar surface activities,” section 2.42, page 8, September 24, 2009

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