Orbital rendezvous using an Augmented Lambert Guidance scheme
Name
67775726-MIT.pdf
Description
Full printable version
Size
13.09 MB
Format
Adobe PDF
Checksum (MD5)
227dec03f4c291e398d693bc60d7ce19
Author(s)
MacLellan, Sara Jean
Advisor(s)
Andrew Staugler and Richard H. Battin.
Date Issued
2005
Publisher
Massachusetts Institute of Technology
Abstract
The development of an Augmented Lambert Guidance Algorithm that matches the position and velocity of an orbiting target spacecraft is presented in this thesis. The Augmented Lambert Guidance Algorithm manipulates the inputs given to a preexisting Lambert guidance algorithm to control the boost of a launch vehicle, or chaser, from the surface of the Earth to a transfer trajectory enroute to the aim point. After the chaser coasts along this transfer trajectory for a time, a manoeuver is performed to match the position and velocity of the target spacecraft. A three degree-of-freedom model was created to simulate the dynamics of the chaser and target spacecraft. The simulation was used to evaluate the ability and versatility of the Augmented Lambert Guidance Algorithm. The analysis proved that the methods developed in this thesis create a feasible algorithm to perform the desired tasks.
Description
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2005.
Includes bibliographical references (p. 121-122).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
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