| タイトル | Titan Explorer Entry, Descent and Landing Trajectory Design |
| 本文（外部サイト） | http://hdl.handle.net/2060/20080013601 |
| 著者（英） | Lindberg, Robert E.; Fisher, Jody L.; Lockwood, Mary Kae |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2006-02-08 |
| 言語 | eng |
| 内容記述 | The Titan Explorer mission concept includes an orbiter, entry probe and inflatable airship designed to take remote and in-situ measurements of Titan's atmosphere. A modified entry, descent and landing trajectory at Titan that incorporates mid-air airship inflation (under a parachute) and separation is developed and examined for Titan Explorer. The feasibility of mid-air inflation and deployment of an airship under a parachute is determined by implementing and validating an airship buoyancy and inflation model in the trajectory simulation program, Program to Optimize Simulated Trajectories II (POST2). A nominal POST2 trajectory simulation case study is generated which examines different descent scenarios by varying airship inflation duration, orientation, and separation. The buoyancy model incorporation into POST2 is new to the software and may be used in future trajectory simulations. Each case from the nominal POST2 trajectory case study simulates a successful separation between the parachute and airship systems with sufficient velocity change as to alter their paths to avoid collision throughout their descent. The airship and heatshield also separate acceptably with a minimum distance of separation from the parachute system of 1.5 km. This analysis shows the feasibility of airship inflation on a parachute for different orientations, airship separation at various inflation times, and preparation for level-flight at Titan. |
| NASA分類 | Lunar and Planetary Science and Exploration |
| レポートNO | AAS 06-077 |
| 権利 | No Copyright |
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