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Flight Project Support

ProjectDateAccomplishment and Impact

Accomplishments: Primary design tool for TESS supporting PDR.

Impact:  First adoption as primary mission support tool. 

OSIRIS-REx Launch Window


Accomplishments: Used GMAT to re-optimize the entire OSIRIS launch window in 1 month of summer intern time.

ImpactImproved convergence properties, and computational time compared to previous software solution.  Project has chosen to use GMAT for this part of the OSIRIS analysis suite.



AccomplishmentsUsed GMAT to re-target OSIRIS Touch-And-Go sequence:  orbit asteroid, phase with asteroid rotation, land on the surface.

ImpactRapid verification of solutions from operational tool and extra validation of GMAT solutions.  GMAT solution is much simpler than implementation in the operational tool.



AccomplishmentsUsed GMAT to investigate possibility  that launch vehicle upper stage could impact earth in the distant future.

Impact:   Saved analyst time.  This type of analysis is easy in GMAT and hard in other tools.



AccomplishmentsUsed GMAT to determine fuel required to change amplitude of the ACE Lissajous.

Impact:   A week of work using GMAT’s optimization methods found equivalent or cheaper solutions than senior design experts using current tools.


AccomplishmentsUsed GMAT for end-to-end  formation modeling and optimization for all phases of MMS mission and for verifying analytical models for reference orbit evolution.    GMAT is now the baseline tool for ground system testing.   

Impact:   GMAT supported mission design for one of GSFC’s most complex missions from MMR through CDR.  GMAT is now the baseline tool for ground system testing.


Accomplishments:  Used GMAT to design optimal maneuvers for ARTEMIS in weak stability orbit regime.   ARTEMIS can only maneuver in the northern s/c hemisphere due to thruster locations.   This was a very difficult design/optimization problem to optimize fuel for weak stability trajectories with severe spacecraft limitations.

Impact: Enabled the mission.  D. Folta commented, “ We could not have flown ARTEMIS without GMAT”.


Accomplishments: M. Mesarch used GMAT to determine optimal maneuvers to rotate the orbital line of apsides and change orbital dimensions.

Impact:  Saved 15% fuel over operational tool solutions and showed that the project’s planned maneuver locations were not fuel optimal.  Fuel savings extended the mission life by ~3 months.


Accomplishments:  Used GMAT to optimize part of the LCROSS launch window analysis, and for post launch re-optimization.

Impact:  Rapid launch window optimization saved time over Copernicus configuration.   Demonstrated that launch injections errors were small enough that re-optimization was not necessary.

Proposal Development Support

Note: For competition sensitive reasons, current proposal support, which is significant, is not listed here.

ProjectDateAccomplishment and Impact



Accomplishments: Used GMAT to design a reference mission for TESS.   Months of analysis in other tools did not find a feasible solution.  A week of part-time work in GMAT found optimal solutions that were 50% cheaper than those found other tools using traditional targeting methods.  Subsequently, a summer student used GMAT to optimize the entire TESS launch window taking only a month of analysis time.

ImpactQuickly found optimal trajectories that met all mission requirements across the launch window when traditional tool struggled.   Significant contribution to proposal effort that won the mission!



AccomplishmentsGenerated optimized Venus trajectories for half of the launch window.

ImpactRapid, easy optimization of integrated trajectories for launch window. 



AccomplishmentsUsed GMAT to generate integrated optimized rendezvous trajectories to comet across the launch window.

Impact:   GMAT optimization resulted in ~100 m/s fuel savings over previous tool.  Demonstrated flexibility in how GMAT can be configured to perform optimization.

 OSIRIS 2007

Accomplishments:  Used GMAT to verify optimal solutions generated by Lockheed Martin in early OSIRIS proposal stages.  Had to include custom constraints on oxidizer tank volume and maximize mass to orbit.

Impact:   Rapid, high fidelity verification (1 week of analyst time) of preliminary solution of Lockheed Martin patched conic optimization tools.

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