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Trajectory Design for the Transiting Exoplanet Survey SatelliteThe Transiting Exoplanet Survey Satellite (TESS) is a National Aeronautics and Space Administration (NASA) mission, scheduled to be launched in 2017. TESS will travel in a highly eccentric orbit around Earth, with initial perigee radius near 17 Earth radii (Re) and apogee radius near 59 Re. The orbit period is near 2:1 resonance with the Moon, with apogee nearly 90 degrees out-of-phase with the Moon, in a configuration that has been shown to be operationally stable. TESS will execute phasing loops followed by a lunar flyby, with a final maneuver to achieve 2:1 resonance with the Moon. The goals of a resonant orbit with long-term stability, short eclipses and limited oscillations of perigee present significant challenges to the trajectory design. To rapidly assess launch opportunities, we adapted the Schematics Window Methodology (SWM76) launch window analysis tool to assess the TESS mission constraints. To understand the long-term dynamics of such a resonant orbit in the Earth-Moon system we employed Dynamical Systems Theory in the Circular Restricted 3-Body Problem (CR3BP). For precise trajectory analysis we use a high-fidelity model and multiple shooting in the General Mission Analysis Tool (GMAT) to optimize the maneuver delta-V and meet mission constraints. Finally we describe how the techniques we have developed can be applied to missions with similar requirements. Keywords: resonant orbit, stability, lunar flyby, phasing loops, trajectory optimization
Document ID
Acquisition Source
Goddard Space Flight Center
Document Type
Conference Paper
Dichmann, Donald J.
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Parker, Joel J. K.
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Williams, Trevor W.
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Mendelsohn, Chad R.
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Date Acquired
June 13, 2014
Publication Date
May 5, 2014
Subject Category
Report/Patent Number
Meeting Information
Meeting: International Symposium on Space Flight Dynamics
Location: Laurel, MD
Country: United States
Start Date: May 5, 2014
End Date: May 9, 2014
Sponsors: Johns Hopkins Univ.
Funding Number(s)
OTHER: 18593-14
Distribution Limits
Work of the US Gov. Public Use Permitted.
Monte Carlo
Libration Point Orbit
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