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Aerocapture navigation at Neptune

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dc.contributor.author Haw, Robert J.
dc.date.accessioned 2006-02-27T21:16:26Z
dc.date.available 2006-02-27T21:16:26Z
dc.date.issued 2003-08-03
dc.identifier.citation AAS/AIAA Astrodynamics Specialists Conference, Big Sky, Montana, August 3-7, 2003. en
dc.identifier.clearanceno 03-2033
dc.identifier.uri http://hdl.handle.net/2014/38813
dc.description.abstract A 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 ΔVLBI 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 (3σ) 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. en
dc.description.sponsorship NASA/JPL en
dc.format.extent 673674 bytes
dc.format.mimetype application/pdf
dc.language.iso en_US en
dc.publisher Pasadena, CA : Jet Propulsion Laboratory, National Aeronautics and Space Administration, 2003 en
dc.subject interplanetary navigation en
dc.subject aerocapture en
dc.title Aerocapture navigation at Neptune en
dc.type Preprint en


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