Optimal Rendezvous and Docking Simulator for Elliptical Orbits

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$69,280.00
Award Year:
2006
Program:
SBIR
Phase:
Phase I
Contract:
NNL06AA56P
Agency Tracking Number:
055158
Solicitation Year:
2005
Solicitation Topic Code:
X4.02
Solicitation Number:
n/a
Small Business Information
Analytical Mechanics Assoc., Inc.
303 Butler Farm Road, Suite 104A, Hampton, VA, 23666-1568
Hubzone Owned:
N
Socially and Economically Disadvantaged:
Y
Woman Owned:
N
Duns:
045856622
Principal Investigator:
Haijun Shen
Principal Investigator
(757) 865-0944
shen@ama-inc.com
Business Contact:
Dennis Bulgatz
Business Official
(256) 830-4811
bulgatz@ama-inc.com
Research Institution:
n/a
Abstract
It is proposed to develop and implement a simulation of spacecraft rendezvous and docking guidance, navigation, and control in elliptical orbit. The foundation of the simulation will be an extension of an existing tool for optimal rendezvous and docking simulations for spacecraft in circular orbit. The existing tool architecture functions in two phases. In the first phase, optimal trajectories are obtained for the point mass model of the docking vehicle subject to path constraints, with the assumption that the target vehicle is in a known, circular orbit. In the second phase of the simulation, the vehicle is considered as a rigid body whose attitude and trajectory is controlled such that the docking port is aligned with the target vehicle at the time of docking, and the flight path follows the optimal trajectory. It is proposed to extend the first phase trajectory optimization capability of this tool to the case when the target vehicle is in an elliptical orbit, and to also add the capability to model rendezvous navigation sensors in order to make use of estimated state feedback rather than true state feedback during the second phase of the simulation.

* information listed above is at the time of submission.

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