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Aerocapture navigation at NeptuneA proposed Neptune orbiter Aerocapture mission will use solar electric propulsion to send an orbiter to Neptune. Navigation feasibility of direct-entry aerocapture for orbit insertion at Neptune is shown. The navigation strategy baselines optical imaging and (delta)VLBI measurement in order to satisfy the flight system's atmosphere entry flight path angle, which is targeted to enter Neptune with an entry flight path angle of -11.6 . Error bars on the entry flight path angle of plus/minus0.55 (3(sigma)) are proposed. This requirement can be satisfied with a data cutoff 3.2 days prior to arrival. There is some margin in the arrival template to tighten (i.e. reduce) the entry corridor either by scheduling a data cutoff closer to Neptune or alternatively, reducing uncertainties by increasing the fidelity of the optical navigation camera.
Document ID
20060043701
Acquisition Source
Jet Propulsion Laboratory
Document Type
Conference Paper
External Source(s)
Authors
Haw, Robert J.
Date Acquired
August 23, 2013
Publication Date
August 3, 2003
Subject Category
Lunar And Planetary Science And Exploration
Meeting Information
Meeting: AAS/AIAA Astrodynamics Specialists Conference
Location: Big Sky, MT
Country: United States
Start Date: August 3, 2003
End Date: August 7, 2003
Distribution Limits
Public
Copyright
Other
Keywords
interplanetary navigation
aerocapture

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