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dc.contributor.authorBevilacqua, Riccardo
dc.contributor.authorRomano, Marcello
dc.date.accessioned2016-12-14T22:25:55Z
dc.date.available2016-12-14T22:25:55Z
dc.date.issued2007-08
dc.identifier.citationBevilacqua, Riccardo, and Marcello Romano. "Fuel-optimal spacecraft rendezvous with hybrid on-off continuous and impulsive thrust." Journal of guidance, control, and dynamics 30.4 (2007): 1175-1178.
dc.identifier.urihttp://hdl.handle.net/10945/50875
dc.descriptionThe article of record may be found at http://dx.doi.org/10.2514/1.27716en_US
dc.description.abstractA Hybrid method is introduced for a minimum-propellant rendezvous and docking maneuver of a spacecraft having both multilevel continuous and impulsive thrusters. We assume that the chaser spacecraft uses a set of independently operated time-continuous low-thrust actuators for the rendezvous maneuvering far from the target and then switches to impulsive thrusters for thedocking maneuver.en_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.titleFuel-Optimal Spacecraft Rendezvous with Hybrid On–Off Continuous and Impulsive Thrusten_US
dc.typeArticleen_US


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