meetings - Space Flight Mechanics Committee

Hopkins University Applied Physics Laboratory. This paper describes the spacecraft and
instruments, the trajectory design, the launch windows and targeting, the post-separation
correction and notional decommissioning plans.
10:45 AAS Ongoing Mission Design Development for the Solar TErrestrial RElations
13-455 Observatory (STEREO)
Christopher Scott, The Johns Hopkins University Applied Physics Laboratory;
Martin Ozimek, The Johns Hopkins University Applied Physics Laboratory
The state of mission analysis for the ongoing Solar Terrestrial Relations Observatory is
presented. Recent developments include the construction of a 20-year predictive ephemeris
that compares modeling sensitivity. Additionally, a detrending analysis was undertaken on
the coefficient of solar reflectivity. Finally, hypothetical mission extension options are
studied given the remaining fuel on each of the spacecraft, including small-body flybys and
Earth-moon system capture. All small-bodies that pass nearby both STEREO satellites are
considered for flyby targeting, and capture trajectories are validated with stability mapping.
High-fidelity end-to-end mission design scenarios are then presented.
11:05 AAS Orbital Accessibility Problem for Spacecraft with a Single Impulse
13-456 Wen Changxuan, Beijing University of Aeronautics and Astronautics; Zhao Yushan,
Beijing University of Aeronautics and Astronautics; Shi Peng, Beijing University of
Aeronautics and Astronautics
Orbital accessibility problem for spacecraft under a single impulsive maneuver was
investigated. The theory of orbital boundary value problem was adopted to attain a
geometrical description of the accessibility condition, which was further converted to an
algebraic proposition. Three typical applications have been suggested: to solve orbital
accessibility problem when both the impulse magnitude and the destination are specified, to
search the minimum impulse required when only the destination is given, and to calculate
the reachable domain when only the impulse magnitude is given. Numerical examples
validated the proposition and demonstrated its three typical applications.
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23 rd AAS / AIAA Space Flight Mechanics Meeting