Navigation analysis and design for Mars entry
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1998.
| Main Author: | |
|---|---|
| Other Authors: | |
| Format: | Thesis |
| Language: | eng |
| Published: |
Massachusetts Institute of Technology
2009
|
| Subjects: | |
| Online Access: | http://hdl.handle.net/1721.1/46645 |
| _version_ | 1826209740949028864 |
|---|---|
| author | Boehmer, Rudy Avi, 1974- |
| author2 | John J. Deyst, Jr. |
| author_facet | John J. Deyst, Jr. Boehmer, Rudy Avi, 1974- |
| author_sort | Boehmer, Rudy Avi, 1974- |
| collection | MIT |
| description | Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1998. |
| first_indexed | 2024-09-23T14:28:20Z |
| format | Thesis |
| id | mit-1721.1/46645 |
| institution | Massachusetts Institute of Technology |
| language | eng |
| last_indexed | 2024-09-23T14:28:20Z |
| publishDate | 2009 |
| publisher | Massachusetts Institute of Technology |
| record_format | dspace |
| spelling | mit-1721.1/466452020-07-07T19:35:43Z Navigation analysis and design for Mars entry Boehmer, Rudy Avi, 1974- John J. Deyst, Jr. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics Aeronautics and Astronautics Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1998. Includes bibliographical references (p. 127-128). This thesis presents a navigation system design for a lander module during entry at Mars. The system estimates the state vector with an extended Kalman filter, which utilizes update information provided by the following measurement types: two-way range with orbiting satellites, two-way Doppler with orbiting satellites, two-way range with surface beacons, two-way Doppler with surface beacons, altitude, and relative surface velocity. Filter performance of the navigation design is analyzed using a computer simulation of such a spacecraft during Mars entry. Simulation results are presented to evaluate the effectiveness of the filter using each of the individual measurement types. In addition, the sequence in which the measurements are filtered that yields the most favourable results is determined. Using this optimal sequence, the simulation produces a final standard deviation of 105.25 m for the lander position and 0.168 m/s for the lander velocity, compared to final standard deviations of 1218.85 m and 3.700 m/s for a case where no measurements are processed. by Rudy Avi Boehmer. S.M. 2009-08-26T17:11:33Z 2009-08-26T17:11:33Z 1998 1998 Thesis http://hdl.handle.net/1721.1/46645 42687400 eng M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission. http://dspace.mit.edu/handle/1721.1/7582 128 p. application/pdf Massachusetts Institute of Technology |
| spellingShingle | Aeronautics and Astronautics Boehmer, Rudy Avi, 1974- Navigation analysis and design for Mars entry |
| title | Navigation analysis and design for Mars entry |
| title_full | Navigation analysis and design for Mars entry |
| title_fullStr | Navigation analysis and design for Mars entry |
| title_full_unstemmed | Navigation analysis and design for Mars entry |
| title_short | Navigation analysis and design for Mars entry |
| title_sort | navigation analysis and design for mars entry |
| topic | Aeronautics and Astronautics |
| url | http://hdl.handle.net/1721.1/46645 |
| work_keys_str_mv | AT boehmerrudyavi1974 navigationanalysisanddesignformarsentry |