@article{jakosky_grebowsky_luhmann_connerney_eparvier_ergun_halekas_larson_mahaffy_mcfadden_et al._2015, title={MAVEN observations of the response of Mars to an interplanetary coronal mass ejection}, volume={350}, number={6261}, journal={Science}, author={Jakosky, B. M. and Grebowsky, J. M. and Luhmann, J. G. and Connerney, J. and Eparvier, F. and Ergun, R. and Halekas, J. and Larson, D. and Mahaffy, P. and McFadden, J. and et al.}, year={2015} }
 @article{prince_dec_tolson_2009, title={Autonomous Aerobraking Using Thermal Response Surface Analysis}, volume={46}, ISSN={["0022-4650"]}, DOI={10.2514/1.32793}, abstractNote={Aerobraking is a proven method of significantly increasing the science payload that can be placed into low Mars orbits when compared to an all propulsive capture. However, the aerobraking phase is long and has mission cost and risk implications. The main cost benefit is that aerobraking permits the use of a smaller and cheaper launch vehicle, but additional operational costs are incurred during the long aerobraking phase. Risk is increased due to the repeated thermal loading of spacecraft components and the multiple attitude and propulsive maneuvers required for successful aerobraking. Both the cost and risk burdens can be significantly reduced by automating the aerobraking operations phase. All of the previous Mars orbiter missions that have utilized aerobraking have increasingly relied on onboard calculations during aerobraking. Even though the temperature of spacecraft components has been the limiting factor, operational methods have relied on using a surrogate variable for mission control. This paper describes several methods, based directly on spacecraft component maximum temperature, for autonomously predicting the subsequent aerobraking orbits and prescribing apoapsis propulsive maneuvers to maintain the spacecraft within specified temperature limits. Specifically, this paper describes the use of thermal response surface analysis in predicting the temperature of the spacecraft components and the corresponding uncertainty in this temperature prediction.}, number={2}, journal={JOURNAL OF SPACECRAFT AND ROCKETS}, author={Prince, Jill L. and Dec, John A. and Tolson, Robert H.}, year={2009}, pages={292–298} }
 @inproceedings{fuller_tolson_2009, title={Improved Method for Estimation of Spacecraft Free-Molecular Aerodynamic Properties}, volume={46}, number={5}, booktitle={Journal of Spacecraft and Rockets}, author={Fuller, J. D. and Tolson, R. H.}, year={2009}, pages={938–948} }
 @inproceedings{tolson_willcockson_desai_thomas_2008, title={Anomalistic disturbance torques during the entry phase of the Mars exploration rover missions: A telemetry and Mars-surface investigation}, volume={56}, number={1}, booktitle={Journal of the Astronautical Sciences}, author={Tolson, R. H. and Willcockson, W. H. and Desai, P. N. and Thomas, P.}, year={2008}, pages={99–119} }
 @article{tolson_bemis_hough_zaleski_keating_shidner_brown_brickler_scher_thomas_2008, title={Atmospheric modeling using accelerometer data during Mars Reconnaissance Orbiter aerobraking operations}, volume={45}, ISSN={["0022-4650"]}, DOI={10.2514/1.34301}, abstractNote={Aerobraking as an enabling technology for the Mars Reconnaissance Orbiter mission was used in numerous analyses based on various data types to maintain the aerobraking time line. Among these data types were measurements from spacecraft accelerometers. This paper reports on the use of accelerometer data for determining atmospheric density during Mars Reconnaissance Orbiter aerobraking operations. Acceleration was measured alongthreeorthogonalaxes,althoughonlydatafromthecomponentalongtheaxisnominallyintothe flowwereused during operations. For a 1-s count time, the root-mean-square noise level was 0:004 mm=s 2 , permitting density recovery to 0:008 kg=km 3 , or about 0.023% of the mean density at periapsis, during aerobraking. Accelerometer data were analyzed in near real time to provide estimates of density, density scale height, orbit-to-orbit variability, latitudinal-seasonalvariations,longitudinalwaves,andotherphenomenainthethermosphere.Summariesaregiven of the aerobraking phase of the mission, the accelerometer data analysis methods and operational procedures, some applications to determining thermospheric properties, correlation with the Mars Global Surveyor and Odyssey missions, and some remaining issues on interpretation of the data.}, number={3}, journal={JOURNAL OF SPACECRAFT AND ROCKETS}, author={Tolson, R. and Bemis, E. and Hough, S. and Zaleski, K. and Keating, G. and Shidner, T. and Brown, S. and Brickler, A. and Scher, M. and Thomas, P.}, year={2008}, pages={511–518} }
 @article{spencer_tolson_2007, title={Aerobraking cost and risk decisions}, volume={44}, ISSN={["0022-4650"]}, DOI={10.2514/1.24303}, abstractNote={Four missions have successfully employed aerobraking at Venus and Mars to reduce the spacecraft orbit period and achieve the desired orbit geometry. The propellant mass reductions enabled by the aerobraking technique allow the use of smaller launch systems, which translate to significant savings in launch costs for flight projects. However, there is a significant increase in mission risk associated with the use of aerobraking. Flying a spacecraft through a planetary atmosphere hundreds of times during months of around-the-clock operations places the spacecraft in harm's way, and is extraordinarily demanding on the flight team. There is a cost/risk trade that must be evaluated when a project is choosing between a mission baseline that includes aerobraking, or selecting a larger launch vehicle to enable purely propulsive orbit insertion. This paper provides a brief history of past and future aerobraking missions, describes the aerobraking technique, summarizes the costs associated with aerobraking, and concludes with a suggested methodology for evaluating the cost/risk trade when considering the aerobraking approach.}, number={6}, journal={JOURNAL OF SPACECRAFT AND ROCKETS}, author={Spencer, David A. and Tolson, Robert}, year={2007}, pages={1285–1293} }
 @article{tolson_keating_zurek_bougher_justus_fritts_2007, title={Application of accelerometer data to atmospheric modeling dunring mars aerobraking operations}, volume={44}, ISSN={["0022-4650"]}, DOI={10.2514/1.28472}, abstractNote={R. H. Tolson∗ North Carolina State University, Hampton, Virginia 23666-6147 G. M. Keating George Washington University, Newport News, Virginia 23602 R. W. Zurek Jet Propulsion Laboratory, California Institute of Technology, Pasadena, California 91109-8099 S. W. Bougher University of Michigan, Ann Arbor, Michigan 48109-2143 C. G. Justus Morgan Research Corporation, Huntsville, Alabama 35805-1948 and D. C. Fritts∗∗ NorthWest Research Associates, Inc., Boulder, Colorado 80301}, number={6}, journal={JOURNAL OF SPACECRAFT AND ROCKETS}, author={Tolson, R. H. and Keating, G. M. and Zurek, R. W. and Bougher, S. W. and Justus, C. G. and Fritts, D. C.}, year={2007}, pages={1172–1179} }
 @article{crowley_tolsont_2007, title={Mars thermospheric winds from Mars Gobal Surveyor and Mars Odyssey aceelerometers}, volume={44}, ISSN={["0022-4650"]}, DOI={10.2514/1.28625}, abstractNote={crowley.pdf, Jan. 2003. [6] Crowley, G., Bullock, M. A., Freitas, C. J., Chocron, S., Hackert, C., Boice, D., Young, L. A., Grinspoon, D. H., Gladstone, G. R., Huebner, W.,Wene, G., andWesterhoff, M., “ANew Surface to ExosphereMars Atmosphere Model,” Bulletin of the American Astronomical Society, Vol. 35, Abstract 14.05, 2003, p. 934. [7] Esposito, P., Johnston, M., Graat, E., and Alwar, V., “Navigation and the Mars Global Surveyor Mission,” Proceedings of the 12th International Symposium on Space Flight Dynamics, ESA SP-403, ESA, Paris, Aug. 1997, pp. 371–376. [8] Esposito, P., Alwar, V., Demcak, S., Graat, E., Johnston,M., andMase, R., “Mars Global Surveyor Navigation and Aerobraking at Mars,” American Astronautical Society Paper 98-384, 1998; also available at http://marsprogram.jpl.nasa.gov/mgs/sci/aerobrake/SFD/SFD-Pa-}, number={6}, journal={JOURNAL OF SPACECRAFT AND ROCKETS}, author={Crowley, Geoff and Tolsont, Robert H.}, year={2007}, pages={1188–1194} }
 @article{baird_tolson_bougher_steers_2007, title={Zonal wind calculations from Mars Global Surveyor accelerometer and rate data}, volume={44}, ISSN={["0022-4650"]}, DOI={10.2514/1.28588}, abstractNote={TheMars Global Surveyor spacecraft was initially placed into a high-eccentricity, nearly polar orbit about Mars with a 45-h period. To accomplish the science objectives of the mission, a 2-h circular orbit was required. Using a method known as aerobraking, numerous passes through the upper atmosphere slowed the spacecraft, thereby reducing the orbital period and eccentricity. To successfully perform aerobraking, the spacecraft was designed to be longitudinally, aerodynamically stable in pitch and yaw. Because the orbit was nearly polar, the yaw orientation of the spacecraft was sensitive to disturbances caused by the zonal components of wind (east to west or west to east) acting on the spacecraft at aerobraking altitudes. Zonal wind velocities were computed by equating the aerodynamic and inertia-related torques acting on the spacecraft. Comparisons of calculated zonal winds with those computed from the Mars thermospheric general-circulation model are discussed.}, number={6}, journal={JOURNAL OF SPACECRAFT AND ROCKETS}, author={Baird, Darren T. and Tolson, Robert and Bougher, Stephen and Steers, Brian}, year={2007}, pages={1180–1187} }
 @article{fritts_wang_tolson_2006, title={Mean and gravity wave structures and variability in the Mars upper atmosphere inferred from Mars Global Surveyor and Mars Odyssey aerobraking densities}, volume={111}, number={A12}, journal={Journal of Geophysical Research. Space Physics}, author={Fritts, D. C. and Wang, L. and Tolson, R. H.}, year={2006}, pages={A12304} }
 @article{wang_fritts_tolson_2006, title={Nonmigrating tides inferred from the Mars Odyssey and Mars Global Surveyor aerobraking data}, volume={33}, number={23}, journal={Geophysical Research Letters}, author={Wang, L. and Fritts, D. C. and Tolson, R. H.}, year={2006} }
 @article{tolson_dwyer_hanna_keating_george_escalera_werner_2005, title={Application of accelerometer data to Mars Odyssey aerobraking and atmospheric modeling}, volume={42}, ISSN={["1533-6794"]}, DOI={10.2514/1.15173}, abstractNote={Aerobraking was an enabling technology for the Mars Odyssey mission, even though it involved risk due primarily to the variability of the Mars upper atmosphere. To reduce the risk, numerous analyses, based on various data types, were performed during operations. The use of one such data type, measurements from spacecrafts accelerometers, for determining atmospheric density during Odyssey aerobraking operations is reported. Accelerometer data were analyzed in near real time to provide estimates of density at periapsis, maximum density, density scale height, latitudinal gradient, longitudinal wave variations, and location of the polar vortex. Summaries of the aerobraking phase of the mission, the accelerometer data analysis methods and operational procedures, applications to determining thermospheric properties, and several remaining issues on interpretation of the data are discussed. Although acceleration was measured along three orthogonal axes, only data from the component along the axis nominally into the flow were used during operations. For a 1-s count time, the rms noise level, derived from the acceleration, varied from 0.07 to 0.5 mm/s 2 , permitting density recovery to between 0.15 and 1.1 kg/km 3 , or about 2% of the mean density at periapsis during aerobraking. Preflight estimates of natural variability based on Mars Global Surveyor accelerometer measurements proved reliable in the midlatitudes but overestimated the variability inside the polar vortex.}, number={3}, journal={JOURNAL OF SPACECRAFT AND ROCKETS}, author={Tolson, RH and Dwyer, AM and Hanna, JL and Keating, GM and George, BE and Escalera, PE and Werner, MR}, year={2005}, pages={435–443} }