Entry Dispersion Analysis for the Stardust Comet Sample Return Capsule

Details Entry Dispersion Analysis for the Stardust Comet Sample Return Capsule Entry Dispersion Analysis for the Stardust Comet Sample Return Capsule

Jan 1997

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1997stin...9726093d&link_type=abstract

Conference Paper, GNC, AFM, and MST

Other

Comets, Earth-Moon System, Monte Carlo Method, Subsonic Flow, High Altitude, Downrange, Attitude (Inclination), Atmospheric Entry, Angle Of Attack, Descent, Timing Devices, Stability, Heating, Education, Deployment

Scientific paper

Stardust will be the first mission to return samples from beyond the Earth-Moon system. The sample return capsule, which is passively controlled during the fastest Earth entry ever, will land by parachute in Utah. The present study analyzes the entry, descent, and landing of the returning sample capsule. The effects of two aerodynamic instabilities are revealed (one in the high altitude free molecular regime and the other in the transonic/subsonic flow regime). These instabilities could lead to unacceptably large excursions in the angle-of-attack near peak heating and main parachute deployment, respectively. To reduce the excursions resulting from the high altitude instability, the entry spin rate of the capsule is increased. To stabilize the excursions from the transonic/subsonic instability, a drogue chute with deployment triggered by an accelerometer and timer is added prior to main parachute deployment. A Monte Carlo dispersion analysis of the modified entry (from which the impact of off-nominal conditions during the entry is ascertained) shows that the capsule attitude excursions near peak heating and drogue chute deployment are within Stardust program limits. Additionally, the size of the resulting 3-sigma landing ellipse is 83.5 km in downrange by 29.2 km in crossrange, which is within the Utah Test and Training Range boundaries.

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