All 2015 Content
Session
Technical Session X: Advanced Technologies II
Abstract
This paper describes the orbital design for ACESat and the trade between instrument stability and continuous access to the star. Three different trajectories are considered for this analysis: Low Earth Orbit (LEO), Geosynchronous Orbit (GEO) and Heliocentric. Uninterrupted stare time to Alpha Centauri is crucial for meeting science requirements; any given orbit requires a 90% minimum access. The instrument thermal stability also has stringent requirements for proper function, influencing trajectory design. However, the driving requirement for mission success centers on the pointing stability of the instrument, with a less than 10 arc second maximum deflection. While other factors come into play, the primary focus is on the reliability and accuracy in acquiring Alpha Centauri within the instrument aperture. Therefore the desired orbit has minimal eclipse durations and should orientate the spacecraft in the sky were there are no interruptions from the instrument to the star system. The optimal trajectory must also accommodate the instrument position on the spacecraft, with constant viewing of the southern portion of the equator available.
Presentation
The Development of a Low Mass Extendible Composite Boom for Small Satellite Applications
This paper describes the orbital design for ACESat and the trade between instrument stability and continuous access to the star. Three different trajectories are considered for this analysis: Low Earth Orbit (LEO), Geosynchronous Orbit (GEO) and Heliocentric. Uninterrupted stare time to Alpha Centauri is crucial for meeting science requirements; any given orbit requires a 90% minimum access. The instrument thermal stability also has stringent requirements for proper function, influencing trajectory design. However, the driving requirement for mission success centers on the pointing stability of the instrument, with a less than 10 arc second maximum deflection. While other factors come into play, the primary focus is on the reliability and accuracy in acquiring Alpha Centauri within the instrument aperture. Therefore the desired orbit has minimal eclipse durations and should orientate the spacecraft in the sky were there are no interruptions from the instrument to the star system. The optimal trajectory must also accommodate the instrument position on the spacecraft, with constant viewing of the southern portion of the equator available.
