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| LEADER |
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| 001 |
in00001661874 |
| 005 |
20220103134507.0 |
| 007 |
cr unu a |
| 008 |
020402s2001 xx a b 000 0 eng d |
| 035 |
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|a (OCoLC)ocm49502863
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| 040 |
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|a TXA
|c TXA
|d UtOrBLW
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| 049 |
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|a TXAM
|a TXAR
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| 099 |
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|a 2001
|a Thesis
|a B79
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| 100 |
1 |
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|a Bryson, Amy Louise,
|d 1974-
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| 245 |
1 |
0 |
|a Optimal command generation for maneuvering the space station /
|c by Amy Louise Bryson.
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| 264 |
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1 |
|a [Place of publication not identified] :
|b [publisher not identified] ;
|c 2001.
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| 300 |
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|a ix, 96 leaves :
|b illustrations ;
|c 28 cm.
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| 336 |
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|a text
|b txt
|2 rdacontent
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| 337 |
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|a computer
|b c
|2 rdamedia
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| 338 |
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|a online resource
|b cr
|2 rdacarrier
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| 500 |
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|a "Major subject: Aerospace Engineering".
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| 500 |
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|a Vita.
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| 502 |
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|b M.S.
|c Texas A&M University
|d 2001.
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| 504 |
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|a Includes bibliographical references (leaves 67-68).
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| 520 |
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|a The objective of this research is to obtain near minimum-fuel and minimum-time maneuver commands for large-angle maneuvers for the international space station. Attitude and angular velocity waypoints are generated using the method of differential inclusion. This approach, motivated by the inverse dynamics method, reduces the dimensionality of the discretized problem to be solved. Different types of control schemes are investigated using a combination of Thrusters and Control Moment Gyros. The optimized controls are determined using standard nonlinear optimization methods from the MATLAB program toolboxes. The maneuvers can be completed using considerably less fuel compared to eigen-axis maneuvers currently being implemented for the International Space Station. The differential inclusion method reduces the need for CMG desaturations as compared to a controller similar to the one on board the International Space Station. The near minimum-time results are comparable to eigen-axis maneuvers. The differential inclusion method is flexible and can easily be modified to accommodate the needs of problems with different constraints. The results obtained in this research use approximate models of the space environment and vehicle dynamics; however, the results can easily be used in a higher fidelity optimization.
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| 530 |
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|a Also available online.
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| 530 |
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|a Issued also on microfiche from Lange Micrographics.
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| 650 |
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4 |
|a Major aerospace engineering.
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| 856 |
4 |
1 |
|u https://hdl.handle.net/1969.1/ETD-TAMU-2001-THESIS-B79
|z Link to OAKTrust copy
|t 0
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| 948 |
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|a cataloged
|b h
|c 2002/4/2
|d c
|e eneff
|f 11:48:16 am
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| 994 |
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|a E0
|b TXA
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| 999 |
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|a MARS
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|t 0
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| 952 |
f |
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|p noncirc
|a Texas A&M University
|b College Station
|c Cushing Memorial Library & Archives
|s cush tdrm
|d Cushing: Theses & Dissertations Microforms (Does not check out)
|t 0
|e 2001 Thesis B79
|h Other scheme
|i computer -- online resource
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| 952 |
f |
f |
|a Texas A&M University
|b College Station
|c Electronic Resources
|s www_evans
|d Available Online
|t 0
|e 2001 Thesis B79
|h Other scheme
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| 998 |
f |
f |
|a 2001 Thesis B79
|t 0
|l Cushing: Theses & Dissertations Microforms (Does not check out)
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| 998 |
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f |
|a 2001 Thesis B79
|t 0
|l Available Online
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