碩士 / 淡江大學 / 航空太空工程學系 / 87 / The purpose of this thesis is to investigate the influence on performance of the proportional navigation missile guidance law. In the terminal guidance system, proportional navigation guidance law has been implemented for years. Various guidance laws were proposed in literatures in the past thirty years, for example, pure proportional navigation, true proporti-onal navigation, optimal proportional navigation and generaliz-ed proportional navigation,…,etc.
At first, we try to evaluate various performance indces among these guidance laws, like acceleration command, energy and time-to-go. Next a heuristic adaptive proportional naviga-tion guid-ance law was suggested through numerical experiences. Numerical examples showed that by letting proportional coefficient be a constant is not a good choice in general.Some literatures used optimal control method to obtain an optimal constant proportional coefficient, however the information requir-ed is more than just line of sight angle, in addition the computation load is heavy. To overcome these severe drawb-acks, a heuristic adaptive proportional navigation guidance law is suggested. Although this method was not derived through a rigorous way. However the results of numerical analysis indicate that this method gives a satisfactory missile acceleration history and utilizes proper energy to intercept target.
Finally, we developed a new guidance law which is used under the constraint of off-boresight angle, which usually occurs in a seeker tracking loop. Numerical examples showed that proposed guidance law provides a strategy to accommodate the above mentioned constraint at the cost of consuming more energy and flight time.
| Identifer | oai:union.ndltd.org:TW/087TKU00295003 |
| Date | January 1998 |
| Creators | Chiou Yuan-Horng, 邱元宏 |
| Contributors | Tyan Feng, 田豐 |
| Source Sets | National Digital Library of Theses and Dissertations in Taiwan |
| Language | zh-TW |
| Detected Language | English |
| Type | 學位論文 ; thesis |
| Format | 79 |
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