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Multi-Impulse to Time Optimal Finite Burn Trajectory ConversionA novel conversion algorithm is presented that combines the fidelity of indirect optimization methods with the generality of direct methods to more easily solve time-optimal, finite-burn pseudo-rendezvous problems. An algorithm is described that converts a set of multiple-impulses, representing the entirety or a portion of a high- or low-thrust maneuver, to an exact time optimal finite-burn trajectory for a thrust limited, constant exhaust velocity spacecraft. A pseudo-rendezvous problem is one that yields a solution whose final time, position and velocity state is equal to that of the original post-impulsive trajectory. An iterative adjoint-control transformation is used to initialize the optimal control two-point boundary value problem. Examples are shown for both high and low-thrust non-coplanar Earth orbit transfers, as well as a low-thrust Hohmann-type Earth-Mars transfer.
Document ID
20200000238
Acquisition Source
Johnson Space Center
Document Type
Conference Paper
Authors
Fogel, J. (NASA Johnson Space Center Houston, TX, United States)
Williams, J. (Jacobs Engineering Group Houston, TX, United States)
Widner, M. (Jacobs Engineering Group Houston, TX, United States)
Batcha, A. (NASA Johnson Space Center Houston, TX, United States)
Date Acquired
January 13, 2020
Publication Date
January 6, 2020
Subject Category
Astrodynamics
Report/Patent Number
JSC-E-DAA-TN69253
Meeting Information
Meeting: AIAA/AAS Space Flight Mechanics Meeting
Location: Orlando, FL
Country: United States
Start Date: January 6, 2020
End Date: January 10, 2020
Sponsors: American Institute of Aeronautics and Astronautics (AIAA), American Astronautical Society (AAS-HQ)
Funding Number(s)
CONTRACT_GRANT: NNJ13HA01C
Distribution Limits
Public
Copyright
Public Use Permitted.
Technical Review
OMB Review

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