The Designs of Coupled Missile Guidance Law and Robust Navigation Constants for the Application of Air Combat Simulation
博士 === 國立成功大學 === 航空太空工程學系 === 102 === The purpose of this dissertation is to combine proportional navigation guidance (PNG) along the pitch-axis and pursuit guidance (PG) along the yaw-axis to derive a three-dimensional coupled missile guidance law with actuator dynamic compensation. A three-dimens...
| Main Authors: | , |
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| Other Authors: | |
| Format: | Others |
| Language: | en_US |
| Published: |
2014
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| Online Access: | http://ndltd.ncl.edu.tw/handle/11859987488144026286 |