Robust Missile Guidance Law Design with Time Delay in Acceleration
碩士 === 國立交通大學 === 電控工程研究所 === 100 === This paper studies the design of missile guidance law using the combination of SMC and ISMC technologies. The presented guidance law is shown to be able to compensate for the presence of uncertainty, including target estimation error, and time lag in acceleratio...
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2012
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| Online Access: | http://ndltd.ncl.edu.tw/handle/17923697511485497596 |
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ndltd-TW-100NCTU54491162016-03-28T04:20:39Z http://ndltd.ncl.edu.tw/handle/17923697511485497596 Robust Missile Guidance Law Design with Time Delay in Acceleration 具加速度時間延遲之飛彈的強健導引律設計 馮仰靚 碩士 國立交通大學 電控工程研究所 100 This paper studies the design of missile guidance law using the combination of SMC and ISMC technologies. The presented guidance law is shown to be able to compensate for the presence of uncertainty, including target estimation error, and time lag in acceleration caused by the flight control system. Besides, the presented scheme possesses a remarkable flexibility of allowing the engineer to select a desired guidance law for the nominal system (i.e., system without uncertainty and time delay) so that the state response of the overall uncertain time delay guidance system is close to that of the selected nominal closed-loop guidance system. Simulation results demonstrate the benefits of the presented scheme. 梁耀文 2012 學位論文 ; thesis 64 zh-TW |
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zh-TW |
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碩士 === 國立交通大學 === 電控工程研究所 === 100 === This paper studies the design of missile guidance law using the combination of SMC and ISMC technologies. The presented guidance law is shown to be able to compensate for the presence of uncertainty, including target estimation error, and time lag in acceleration caused by the flight control system. Besides, the presented scheme possesses a remarkable flexibility of allowing the engineer to select a desired guidance law for the nominal system (i.e., system without uncertainty and time delay) so that the state response of the overall uncertain time delay guidance system is close to that of the selected nominal closed-loop guidance system. Simulation results demonstrate the benefits of the presented scheme.
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| author2 |
梁耀文 |
| author_facet |
梁耀文 馮仰靚 |
| author |
馮仰靚 |
| spellingShingle |
馮仰靚 Robust Missile Guidance Law Design with Time Delay in Acceleration |
| author_sort |
馮仰靚 |
| title |
Robust Missile Guidance Law Design with Time Delay in Acceleration |
| title_short |
Robust Missile Guidance Law Design with Time Delay in Acceleration |
| title_full |
Robust Missile Guidance Law Design with Time Delay in Acceleration |
| title_fullStr |
Robust Missile Guidance Law Design with Time Delay in Acceleration |
| title_full_unstemmed |
Robust Missile Guidance Law Design with Time Delay in Acceleration |
| title_sort |
robust missile guidance law design with time delay in acceleration |
| publishDate |
2012 |
| url |
http://ndltd.ncl.edu.tw/handle/17923697511485497596 |
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AT féngyǎngjìng robustmissileguidancelawdesignwithtimedelayinacceleration AT féngyǎngjìng jùjiāsùdùshíjiānyánchízhīfēidàndeqiángjiàndǎoyǐnlǜshèjì |
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